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H^V^V^ 



^ SD72-SH-0060 

VOLUME 1M 


AERODYNAMIC 


DESIGN DATA BOOK 


VOLUME 1 


ORBITER VEHICLE 


STS-1 


SDM BASELINE 



CONTRACT No. NAS9-14000 
IRD SE640T2 
WBS No. 1. 2.2.1 . 1 



ks 



TYPE 2 DOCUMENTATION 



Spact Transportation System 
Integration A Operations Division 

Space Systems Group 



• 



Rockwell 
International 



i^oa 




Spaca Systems Group 



0$ 



Rockwell 
International 



SYSTEM DEFINITION MANUAL CHANGE LOG 



AUTHORITY 



DATE 



CHANGE SUMMARY 



APPROVAL 



N/A 



Nov. '8C 



Release of Volume 
STS-! AERODYNAMIC 
NOTE: This release is 

Volume 11-5. 

DO NOT DESTROY VOLUME 



1M 

DESIGN DATA BOOK 
IN ADDITION to 



1L-5. 



Coord . with 
T .E .SurberJ^ 
W .E . Borneman 
A .M.Lee'^^; 







SOM COOE NO. A.i 



l-A- 



SD72-SH-0060- 1M 



Space Syslems Group 



* 



Rockwell 
International 



DISTRIBUTION LIST FOR SD72-SH-00 60 - 1 



AERODYNAMIC DESIGN DATA BOOK, Volume 

(SE640T2) 



W. 

T. 

W. 

D. 

H. 

D. 

F. 

D. 

T. 

D. 

J. 

W. 

L. 

F. 

S. 

L. 

P. 

R. 

J. 

C. 

J. 

G. 

R. 

P. 

W. 

D. 

M. 

R. 

R. 

C. 

K. 

E. 

J. 

M. 

J. 

J, 

D, 

E 

B 

G 

J 

J 



E. Bornemann 

E. Surber (2) 
R. Russell 

C. Schlosser 
S. Dresser 

F. Dominik 

F. Fitzgerald 
C. Olsen 

A. Petrick 

G. Duhnke 
S, Stone 
M. Zeman 
M. Gaines 
S. Laspesa 

Kraus 
P. LeBlanc 
L. Lemoine 
H. Spangler 
R. Austin 
M. Linger 
A. Hill 
P. Bayle 
8. Lyford 
M. Schwartz 
L. Schleich 
A. Johnson 
L. Gredberg 
L. Powell 
H. Lassen 
F. Warner 
V. Anderson 



N. Spryer 
H. Johnson 
R. Schall 

E. Emons 

F. DeYulia 

E. Wood 

L. Freddol ino 
L. Lum 
M. Minott 

F. Thompson 
F. Yoder 



AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

AC07 

FB53 

FB53 

FB53 

FC95 

FB53 

FB53 

FB53 

FB75 

ABit7 

SK25 

AC56 

AC95 
AC9 1 * 
lkC3k 
AERO 
AD73 
AD73 
AB79 
OA35 
FB37 
FB75 
FC95 
ZA01 
ZC01 



ORBITER VEHICLE 



SDM DISTRIBUTION 



L. 


M. 


Cloyd 


ZC01 


R. 


A. 


Boudreaux 


AD75 


J. 


J. 


Gutsmiedl 


FA*»6 


H. 


C. 


Hartzel 


AC25 


S. 




Kreidel 


AA33 


C. 


J. 


McNamara 


ZK<*fl 


W. 


L. 


Owens 


FA95 


W. 


B. 


Fouts 


FB9^ 


J. 


M. 


Robertson 


DA25 


P. 


C. 


Merhoff 


ABR3 



(jsc)d) 



(KSC)(1) 



D. L. Fernandez FC50 



CS Draper Labs, 
555 Technology Square 
Cambridge, Mass. 02139 
S. TAVAN, Mail Station 71 



Data Management (5) 
See IRD 199 Form for External Distribution 



'fllfe Rockwell 
^ International 

SPACE SYSTEMS GROUP 



REPORT No.= SD72-SH-O06O 







'*S|ffc 



TITLE: 



AERODYNAMIC DESIGN DATA BOOK 
VOLUME I, ORBITER VEHICLE 



CHANGE NOTICE 



REVISION No.: 1M 



REVISION DATE: 
Page 1 of _J 



REVISION RECORD 



REV 



DATA RELEASE DESCRIPTION 



APPROVAL 



DATE 



t 4j.&*~-*~*— ' 



M 



Release of Volume IM, STS-1 AERODYNAMIC DESIGN 
DATA BOOK 

NOTE: This release is IN ADDITION to Volume 1L-5 
DO NOT DESTROY VOLUME 1L-5 



W.E. Bornemann 
Mgr. Aerodynamics 



lov M 



"i -b- 



SD72-SH-0060-IM 




FOREWORD 

The Rockwell Space Shuttle is a combination air- 
craft-spacecraft designed to launch a variety of 
payloads into Earth orbit and/or retrieve payloads 
from orbit, return to Earth, and land in the manner 
of conventional aircraft. The Space Shuttle Vehicle 
is comprised of three major elements; the Orbiter 
Vehicle, External Tank, and Solid Rocket Boosters. 
Since the flight vehicle is a combination aircraft- 
spacecraft, its external features are designed to 
provide the protection and versatility for both 
space and atmospheric flight regimes. This partic- 
ular volume provides the aerodynamic characteristics 
for the Orbiter Vehicle. 




Span Transportation System 

Integration & Operations Division 

Spac* Systems Group 



'1* 



Rockwell 
International 



-i-C 



SD72-SH-O060-1M 



'1* 



Rockwell 
Space Systems Group ^J^ International 



PREFACE 

The purpose of this book is to present the STS-1 Orbiter Vehicle aerodynamic 
design data appropriate to full-scale flight performance and stability and 
control analyses. The data include configuration descriptions, aerodynamic 
force and moment coefficients (both static and dynamic), and control effec- 
tiveness. Data are provided throughout the flight speed regimes from subso- 
nic to hypersonic and high altitude; rarefied atmospheric effects are pro- 
vided as are the effects of aeroelastic deformation and reaction control 
flow-field interactions. 

The book has been prepared to meet the needs of system design and analysis 
engineering, loads and structural engineering, performance analyses, and 
manned simulation studies. Data are based on the results of wind tunnel 
tests of various scale models of the Orbiter Vehicle, Model support system 
tare effects have been determined for corrections to provide, essentially, 
support-free aerodynamic characteristics. Corrections have also been made 
(where appropriate) for scale effects (Reynolds number) and for non-represen- 
tation of actual full-scale geometric features such as small protuberance 
items, thermal protection system tile steps and gaps, surface roughness, 
and the like. All data are provided in a format which will allow a build- 
up from a basic configuration by means of contributing elements to each 
force or moment component such as control surface effectiveness, landing 
gear effects, etc. Data are presented in a manner which treats each force 
and moment separately and equations are provided to facilitate the build-up 
procedure, transfer of data to moment reference centers other than the basic 
reference center (most forward center-of -gravity location), and account for 
the effects of aeroelastic deformation, rarefied atmosphere, and combined 
reaction control -aerodynamic control in the low dynamic pressure regions. 

This report has been prepared at the express direction of the NASA for a 
dedicated STS-1 Aerodynamic Design Data Book. The basic aerodynamic data 
were reviewed by JSC, ARC, IRC, and ARO-AEDC prior to its release. Particu- 
lar attention was given to the transonic and supersonic flight regimes. 
Various interaction data, providing the bridging between viscous data and 
orbital aerodynamic characteristics, were supplied by LRC and JSC. Rockwell 
and JSC coordinated the approach and landing flight test results for incor- 
poration into the low speed data. The Aero Technical Panel members (JSC, 
LRC, ARC, AEDC, and DFRC) all contributed to the data for this report. 

Rockwell engineers under T. E. Surber (Supervisor) and D. C. Schlosser (Lead 
Engineer) prepared and analyzed the data with primary responsibilities going 
to D. C. Olsen, W. M. Zeman, D. G. Duhnke (longitudinal), F. F. Fitzgerald, 
H. Parrell, L. L. Landrum (lateral-directional), H. Parrell, F. C. Chinn (hinge 
moments), D. F. Dominik, K. F. Anderson (aeroelasticity ), H. S. Dresser, 
Y. H. Kim, J. S. Stone, G. V. Owens (RCS). Digitized data, data tapes, and 
figures were the responsibilities of D. F. Dominik, J. M. Kelleher, T. Petrick, 
M. Kallanse, and G. V. Owens. The typed manuscript was prepared by Muriel Burke 
and Terri Harrison. 



pfc SHo^ 



W. R. Russell: Editor £+ ^ 



Downey, California 
1980 




-ii- 



°*B,ll* 




#1* 



Rockwell 
Space Systems Group ^X"^ International 



, ■ , , ^ ^ ^ 5T5-1 

CONTENTS 



PAGE 

REVISION RECORD a 

FOREWORD ' 

PREFACE !i 

iii 



CONTENTS < 

NOMENCLATURE v 

INTRODUCTION • • vi ' ' 

INCORPORATION OF REV1EV ITEMS ix 

1.0 ORBITER MISSION '- ' 1 

1.1 Mission Description \'n'l 

1.2 Mission Capability \n'l 

1.3 Flight Test 1.0-5 

2.0 GROUND RULES 2 - "' 

2.1 Design Ground Rules I'n'l 

2.2 Flight Envelopes/Conditions 2 • " , 

3.0 CONFIGURATION DESCRIPTION 3-0-1 

3.1 Conflguration(s) and Dimensions. . , 3 A°T, 

3.2 Reference Axes and Sign Conventions \'n'\\ 

3.3 Aerodynamic Control \'n'\l 

3.4 Landing Gear and Ground Clearance ;'«",, 

3.5 Thermal Protection System >. *'°"" 

3.6 Reaction Control System i'n" n 

3.7 Air Data System \ n'-lU 

3.8 Crew Escape System ,n ?* 

3.9 Shuttle Infrared Leeside Temperature Sensor i'n 26 

3.10 Mass Properties 10- 27 

3.11 Surface Design Requirements J.u */ 

it.O ORBITER VEHICLE AERODYNAMIC DATA '♦- " 1 

k I - 1 
4.1 Longitudinal Aerodynamics 

I».l.l Body-Axis System 4.1.1-1 

A. 1.1. 1 Normal Force Coefficient it. 1. 1.1-1 

I). 1.1. 2 Axial Force Coefficient ?'!',, 

O.I.3 Pitching Moment Coefficient .... 4.1.1.3-1 

it.1.1.4 Trim and Stability *t . 1 . 1 .*»-! 

I4.I.2 Stability-Axis System A. I. 2-1 

1.. 1.2.1 Lift Coefficient M'M~! 

it. 1.2.2 Drag Coefficient . / , , , 

4. 1.2.3 L!ft-to-Drag Ratio <t. 1.2. 3-1 

I4.2 Lateral-Directional Aerodynamics 4.2-1 

It. 2. 1 Body-Axis System !*'?'!"! , 

4.2.1.1 Side Force Coefficient t, , 

It. 2. 1.2 Yawing Moment Coefficient • . • ■ «... 1.2-1 

4.2.1.3 Rolling Moment Coefficient 1 .... 4.2. I. 3"' 

It 3-1 
t» . 3 Crew Escape System • 

it. 3.1 Body Axis System ... 4.3.1-1 

it. 3. 1.1 Normal Force Coefficient .... 4.3.1.1-1 

4.3.1.2 Axial Force Coefficient ..... 4.3. I. 2-1 

4.3.1.3 Pitching Moment Coefficient .... 4.3.1.3-1 

it. 3. 1.4 Side Force Coefficient 4.3.l.it-l 

it. 3. 1.5 Yawing Moment Coefficient 4.3.1.5-1 

it. 3. 1.6 Rolling Moment Coefficient it. 3. 1.6-1 

-i i i- 

SD72-SH-O06O-- 1M 



* 



Rockwell 
Space Systems Group WA^J International 



CONTENTS (continued) Page 

5.0 AERODYNAMIC HINGE MOMENT COEFFICIENTS 5.1-1 

5.1 Elevon Control Hinge Moment Coefficient 5.1-1 

5.2 Body Flip Control Hinge Moment Coefficient 5.2-1 

5.3 Rudder/Speed Brake Control Hinge Moment Coefficient 5.3-1 
6.0 AERODYNAMIC DATA UNCERTAINTIES 6.0-1 

6.1 Longitudinal Aerodynamics 6.1-1 

6.2 Lateral-Directional Aerodynamics 6.2-1 

6.3 Hinge Moments 6.3-t 
i.k Crew Escape System 6.4-1 

6.5 Ground Effects 6.5-1 

6.6 RCS Tolerances 6.6-1 

6.7 Asymmetric Uncertainties 6.7-1 

7.0 REFERENCES and BIBLIOGRAPHY 7.0-| 
APPENDICES 

A. AEROELASTICITY A-l 

B. RCS FLOWFIELD INTERACTIONS B-l 

C. HIGH ALTITUDE AERODYNAMICS C-l 
(Including Orbital Aerodynamic Characteristics) 

D. DATA TAPE USAGE 0-1 

E. 07102 ASYMMETRIC AERODYNAMICS E-l 



-I V- 



W 



SD72-SH-O06O- 1M 




Spaca System* Group 



* 



Rockwell 
International 



NOMENCLATURE 



A. ACRONYMS 

ACS 
A OTA 
AFC5 
AMI 
A/S 

3FCS 

CC3 
CDR 
CEI 
CSS 

OFI 
DOF 

eafb 

ST 
ETR 

F 

FAA 

FCF 

■cs 

FF 

FMOF 

FOF 

FRC 

FRF 

FRR 

FSSR 

FTR 

ON&C 

HAC 
Mil 
HSI 
HW 

I 



JSC 

KEAS 
XSC 



MDM 
Wl 
MMLE 
.IRC 

NAV 

OFI 

QF7 

cms 
ov 

PDR 
PTI 

9CS 
RIO 
RSS 

SILTS 

SPI 

S?S 

SR9 
5/C 
STC 



ACROhYHS (Continued 



Ai r 3*ta Sy*t*m 

Air Data Transducer Assembly 

Automatic Flight Control System 

Alphe-Haeh Indicator 

A i rs p««d 

Backup Flight Control System 

Configuration Control 3oard 
Critical Cesign Raviaw 
Contractor End I tan 
Control Stick Steering 

:evelopment Flight In* t ruflientat ion 
Deg reels) -of- Freedom 

Edward* Air Fore* 3a*e 
External Tank 
Ea*t*m Ta*t Rang* 

Ferry 

Federal Aviation Agency 

Functional Checkout Flight 

Fl ight Control Sy»t*m 

Fr«*-FI ignt 

Flr*t Manned Orbital Flight 

F! rst Operational Flight 

Flight Ra»*areh Cantar 

Fligni Raadln*** Firing 

Flight Raadina** Review 

Functional Sub*yst*m Software Reg u I reman t 

Flight Te»t Requirement 

Guidance, Navigation, and Control 

Heading Alignment Circle 
Handl ing Hualltle* 
Horizontal Situation Indicator 
Head Wind 

Inert 
• Initrument Landing Syitem 

Johnson Space C«nter 

Knotj-Eouivalent Ai rspeec 
Kennedy Spec* Cantar 

Lauren Panicle 

Manned 

Modulate-Demodulate 

Master "eajurement List 

Modified Maximum LIklinooo Estimate 

Moment Reference Center 

Nevigatlan (System) 

"oerational e lignt instrumentation 
3rfc i ta I Fl ; ght "est 
Orsital Maneuvering System 
Orsi ter Venicle 

Preliminary Design Review 
Programmed Test Input 

Reaction Control System 
Peview I tern Disposition 
Soot-Sum-Square 

Shuttle Infrared Leesld* Temoeratur* Sensor 

Surface Position Indicator 

Samples 3er Second 

Sol id docket Booster 

Spacecraft or ScaDility and Control 

Supplemental Type Certificate 



TAEn 

TO 

TOGW 

TPS 

TBO 

T/U 

UHF 

VFT 
VHF 
VOR/LOC 

<TR 
GENERAL 



9L 

SP 

F 



FRL 
FRP 
F5 

ij or rl 



R 
ReN 



Terminal Area Energy "anagement 

Take-Off 

Take-Of 3ro*s Weight 

Thermel Protection System 

To Be Determined 

Thru* I- to -We ight Ratio 

Ultra-High Frequency 

Vertical Fl ight Te*t 

Very-High Frequency 

Visual Omni -Range/Local izer 

Western "est Range 



Acceleration 't/see l (also g's) 

Subscripts: X axial 

Y lateral 
Z normal 

Buttock Line 
Buttock Plane 

Center! In* 

Force ,b 

Subscripts: (see Acceleration, aoove) 

Fuselage Reference Line 
Fuselage Reference Plane 
Fuselage Station 

Hinge line 

Hach Number 
Subscripts: 

Pre*»ur* 
Subscripts: 



dive 
NO maximum operating 

ibj/ft 2 (p»f) 
■ ambient \or freestream 
s static 
T '.ota I 



SL t 



sea level 



"F, '*, or '* 



-L 

«P 

wop 



Universal Sas Constant 
Reynolds Numoer 

"effperatura 
Thrust 
Thrustl Ine 



velocity ^« ar <r0 " 

j linear pertjrbed velocity aicng 

x-»xls 'oosi tlv* 'or-ara) 
■i linear lerturoed /eioeitv aicng 

y-axis !pc*ltlv* out -ignt «ingj 
w linear perturbed velocity along 

z-axls '-osiciv* iownwardl 

Suoscripts: c calibrates 

e tquivalent 

i Incicated 

9 dive 

MCA minimum control In air 

"C3 minimum control r>n jrjund 

mO -aximum operating 

- 'reestream 

Viscou* Parameter 

Weight 
Water I ine 
Water 9 lane 
Wing latum P 1 ane 



'55 



-v- 



SD72-SH-0060-1M 



Space Systems Group 



* 



RocfcweH 
intemadonai 



3. GENERAL ( Con c I nu«d ) 



a 
a.e. 



=9 
ep 



Speed of Sound in Mr 
Aerodynamic Center 



ft/see or knots 



Spaa ft 

Chord Inches 

or MAC - maan aerodynamic chord 

Subscripts: bf body flap 

a elevon 

r rudder 

sb speed brake 

w wing 

Center of gravity 
Center of pressure 

Acceleration due to gravity ft/sec 1 

Altitude (er heignt) ft or nautical miles 

Mass slugs 

Load Factor g's 

dynamic pressure » 1/2S" 1 lb/ft 1 (psf) 

time sacs, "Ins, hrs 

Increment 

Mondlmenslonal change In HRC with regard 
to UP; (Z^,.- Z^/e 
■i* 

(1) Semi-Span Parameter - y/b/2 
(2)' Flexible-to-Rlgid Ratio 



Incidence 
Sweep Angle 
Taper Ratio 
Mean Free Path 



degrees 
degrees 

Inches 



Nondimeni tonal change to MRC with 
regard to Fuselage Station 



(1) Mass density of ai r 

(2) Correlation Coefficient 



slug/ft 1 



(1) Ratio of freestream density at a 

given altitude to standard sea 
level air density 

(2) Standard Deviation 



Frequency 

Angle 

Greater than 
less than 



H (eye lei/see) 



C. CONFIGURATION 

Lg Body Length 

IE 
5 



inches 



Leading Edge 






Reference Area 






Subscripts: 


a 


ai leron 




bf 


Dcdy flap 




a 


elevon (elevator) 




r 


rudder 




sb 


speed brake 




w 


wing 




V 


vertical tail 



TE 
X 

y 



Trai I ing Edge 
Longitudinal axis 
Lateral axis 
Vertical axis 



(I) Control Surface Deflection 
Subscripts: 



degrees 



a aileron (positive 
for poll tive rol I- 
!ng moment) 
bf body flap (positive 
for nojedewn pitch- 
ing moment) 

e elevon (positive for 
Closedown pitching 
moment) 

r rudder (positive for 
nose-left yawing 
moment) 
sb speed brake 



(2) Dihedral Angle 
MOMENT S PRODUCTS OF INERTIA 



Moment of Inertia 
I , ro 1 1 1 ng 
l„ pitching 



Product of inertia 



'xr ' xz" 



YZ 



FORCES 
A 

c. 



Axial; aerodynamic force along 

the X-body axis (positive aft) 
Axial force coefficient • A/q"S 

Drag; aerodynamic force along the 
total velocity vector in plane of 
symmetry (positive aft) 

Drag coefficient • 0/^5 

Lift; aerodynamic force perpen- 
dlcular to total velocity vector in 
plane of symmetry (positive .pward) 

Lift coefficient ■ 1/^5 

Normal; aerodynamic force along the 
Z-body axis (positive upward) 

Normal force coefficient • N/TS 

Side; aerodynamic force along :he 
Y-bOdv axis (positive out rignt 
wing) 

Side force coefficient - y/5"5 



degrees 



slug-ft 1 



slug- ft 2 



pounds 



pounds 



pounds 



pounds 



-VI- 



enii-cn.nfisn. im 



Spac* Systems Group 



w}$ 



Rockwell 
International 



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SD72-SH-0060 1M 




#1% 



Rockwell International 

Space Division 



1.0 ORBITER MISSION 

The Rockwell Space Shuttle Orbiter is designed to launch a variety of 
Jayloads Into (and/or retrieve from) earth orbit The Orbiter Veh.cl. 
will be launched in a vertical attitude and landing will be accomplished 
in a horizontal manner similar to conventional aircraft. 



1.1 



IXTII VIHKII 




'tlTHMM U«* 



ITaunch configuration 




MISSION DESCRIPTION. The Space 
Shuttle mission is summarized in 
Figure 1.1-1. Following fl ight 
readiness and checkout, the 
Space Shuttle will be launched 
by means of solid rocket boosters 
(SRB) and an external tank (ET) 
as shown in the sketch. 

Maximum payload capability is 

65.000 pounds for an easterly . . 

launch from the Eastern Test Range (ETR) at Kennedy Space Center (KSC) 

and 32,000 pounds for a polar orbit 

launch from the Western Test Range 

(WTR) at Vandenburg Air Force Base. 

Subsequent to separation from the ET, 
the Orbiter Vehicle wi H be inserted 
into earth orbit where a payload may be 
deployed and/or retrieved. The Orbiter 
Vehicle can also function as a space 
laboratory for a moderate duration and 
will provide accommodations for up to 
five mission specialists in addition to the normal crew of commander and 
co-oiTot An on-orbit stay period of seven days is required and could 
be extended for up to 30 days during the operational phase of the program. 

After completion of the orbital operations phase deorbit is accomplished 
by retro-fire of the Orbital Maneuvering System 0MS and the Orbiter 
descends to the atr^spheric entry Interface <" om "''Vnlm.: Dr«Ju« 
hOQ 000 feet) The initial entry phase extends to a dynamic pressure 
Uvel of 20 p f (approximately 250,000 feet) during which RCS attitude 
cont ol from two aft 0MS pods is blended with aerodynamic surface con- 
trofs the Utter gaining in effectiveness as dynamic pressure increases. 

The entrv flight phase, from a dynamic pressure level of 20 psf to a Mach 
\Jl If i-fthan five Is accomplished at a high angle of attack during 

„ „ ', n conjure ion witn vehicle speed, can resul t in rel at.ve y arge 
'. -..iriallv derived ail- data, probes are extended (M " 3.5) to 
' L ,i da a IlatWe to the vehicle. During a typical nor»a entry, 

rang, control *" acn"v.d by bank angle „ni >e angle of attack follows a 



1.0-1 



SD72-SH-0060- 1M 



'1* 



Rockwell International 

Space Division 



predetermined schedule to achieve (at approximately M - 1.5) an angle 
somewhat smaller than that corresponding to maximum L/D. A down range 
capability of up to 4300 nautical miles with a cross range capability of 
980 nautical miles may be realized. 

Equilibrium subsonic gliding flight is achieved at an altitude of 
approximately 40 r 000 feet* Range control during the gl iding descent is 
obtained by angle of attack modulation wi th velocity control maintained 
by the speed brake. The approach and landing interface occurs at 10,000 
feet above ground level and a preflare Is Initiated at an .appropriate 
altitude, followed by a deceleration float and touchdown. . The initial 
approach target and flare altitude will be scheduled to provide a mini- 
mum of 25 seconds between flare initiation and touchdown. 

Representative time histories of five trajectory parameters —altitude, 
relative velocity, flight path angle, total load factor , and dynamic 
pressure — are shown in Figure 1.1-2. These time histories represent a 
high cross range return from a 100-nautical mile orbit with a 25,000- 
pound pay load and an aft center of gravity. The trajectory (TPS design 
number l¥»lA) Is presented for the purpose of illustration only. 

More complete and detailed mission data are avai lable in the Mission 
Data Book, Reference 1-1. Detailed descriptions of launch trajectories 
are given In References 1-2 .and .1-3 -and .additional .entry trajectory data 
may be obtained from Reference \-k. References 1-5 and 1-6 contain de- 
tailed information relative to separation and abort. 



EXTERNAL TANK 
SEPARATION 





/RETURN TO 
U.AUNCH SITE 

LAUNCH \« 



*xOR8IT INSERTION ORBITAL OPERATIONS 

OEORBIT 



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IMPACTOF 
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SPACE SHUTTLI MISSION 



1.0-2 



972-SH-0060-1M 



4* 



Rockwell International 

Space Division 




MM III 
• AllllMI tffMINCI MISSIONS 



1.2 MISSION CAPABILITY. The Orbiter Vehicle "mission capability envelope" 
is defined by four baseline 
reference missions. Table 
1.2-1 summarizes these base- 
line missions. From the 
standpoint of entry, these 
become essentially two types 
of missions — a ramped 
angle of attack, character- 
ized by long range and high 
cross range and a high angle 
of attack characterized by 
short range and small cross 
range. Typical trajectories 
representing these two 
missions are presented in 
Figure 1.2-1 for the former 

(typical of mission 1) and Figure 1.2-2 for the latter (typical of 
mission 3B) . Orbital Flight Test (OFT) requirements should fall within 
the baseline reference mission envelope of capability. 



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Space Division 



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1.3 FLIGHT TEST. The Orbital Flight Test (OFT) program. Is designed to sub- 
stantiate the aerodynamic design of the Orblter Vehicle throughout the 
expected flight regime. Flight test plans will be developed to satisfy 
multiple test objectives and to obtain a maximum data return. Testing 
will be consistent with the planned missions so that, insofar as 
possible, direct comparisons can be made. Verification of the aero- 
dynamic design data will be accomplished by comparing the flight test 
derived aerodynamic data with results predicated on wind tunnel testing 
as presented in this report. The aerodynamic design data book will then 
be updated to reflect the flight results. 



1.0-4 



SD72-SH-0060-IM 




0$ 



Rockwell International 

Space Division 



2.0 GROUND RULES 

Major program requirements influencing the aerodynamic design of the 
delta wing Orbiter are defined In the Space Shuttle Program Request for 
Proposal as modified by SD MCR No. 0200 and Revisions (References 2-1 and 
2-2). On March 3, 1975, MCR 1750 was initiated to replace MCR 0200. The 
former MCR, "Shuttle Baseline Control Drawings," assumed the function of 
the latter and will be revised (as required) to authorize release of 
baseline drawing changes. 



2.1 DESIGN GROUND RULES, 
Table 2.1-1. 



Aerodynamic design ground rules are summarized in 



Tobl. 2.1-1 AERODYNAMIC 0ES1GH GROUND RULES 



PARAMETER 


VALUE 


ANGLE OF ATTACK 
Hypertonic 
Supersonic 
Transonic 
Subson 1 c 


25" to 50* 
0* to 25' 
0* to 15* 

-5* to 20* 


LONGITUDINAL STABILITY 
STATIC MARGIN 

Hypersonic (Minimum) 
Subsonic (Minimum) 

(Aft Center of Gravity) 


Pos 1 1 1 vc 

•tX L. 

{•$.k$X MAC) 


CENTER OF GRAVITY RANGE 
Design Range 
Minimum Travel 


0.6501. 'o 0,6751, 
2*1. 


LlfT/DRAC MODULATION 
Subsonic Value - Peak 
(Geer-Up, «„ - 0') 
(Gear-Up. «„ - 85") 


Not lest than *.* 
Not lest than 2.5 


LANDING PERFORMANCE 
MINIMUM 0ESISN TOUCHDOWN SPEED (V fl ) 
LANDING WEIGHT (WITH PAY10AD) 
PAYL0AD 


171 knots 

187,500 pounds 
32,000 pounds 



2.2 



FLIGHT ENVELOPES/CONDITIONS. Figure 2.2-1 presents the design center of 
gravity limits and static margin limits. A summary of the trim limits 
of Section k.\.\.k is also shown on the figure. The summary trim limits 
are baseS on the TPS design trajectory IWHJ angle of attack schedule 
(also given In Section I».1.1.M. 



2.0-1 



SD72-SH-0060-1M 



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Rockwell International 

Space Division 



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Space Division 



3.0 CONFIGURATION DESCRIPTION 

The Orbiter Vehicle is configured to perform as both a spacecraft and an 
aircraft To this end, the vehicle must provide the protection and 
versatility necessary for both orbital and atmospheric flight operations. 
DesTgn of the vehicle is such that it will meet all requirements as set 
forth in the Orbiter Vehicle End I tern Spec, fi cat , on (Reference 3"1)- 
Figure 3-0-1 presents a general arrangement, three-view drawing o the 
Orbiter Vehicle with reference dimensions and areas tabulated on the 
f i gure. 





























»^^^ 






i,m»i1 



•■>. MM IIMS1K, I, 



STATIC OtOUHD KNI 




Atmosoheric (or aerodynamic) requirements are predicated, for the most 
quirements depicted in Figure 3-0-2. 



3.0-1 



SD72-SH-0060-1M 



*J> 



Rockwell International 

Space Division 



MAXIMUM LANOING SPEED 

OCT DISPERSION ♦ 10 KNOT TAILW1NDI 



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TOUCHDOWN 

VELOCITY 

(KEAS) 



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MINIMUM 

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WEIGHT (32.000 POUND 
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WEIGHT 

MS.0O0POUN0 

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ORBITER LANOING WEIGHT (1000 L8I 



HOT DAY AT SEA LEVEL 
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GROOVED RUNWAY 
REQUIREMENT 



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TOUCHDOWN VELOCITY (KNOTS TRUE GROUND SPEED! 



Figure 3.0-2 LANDING REQUIREMENTS 



Evolution of the Orbiter Vehicle configuration from Authority to Proceed 
(ATP) to the present time is summarized in Figure 3.0-3. Major parameters 
influencing the design are noted on the figure. 



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Figure 3.0-3 ORBITER VEHICLE EVOLUTION 



3.1 CONFIGURATION ANO DIMENSIONS. The configuration was selected to achieve 
high cross range aerodynamical ly and to be capable of trimmed flight over 
a wide range of angles of attack. The double-delta wing planform com- 
bined with a moderately low fineness ratio (approximately 5) body minimizes 



3.0-2 



SD72-SH-0O6O-1M 



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Rockwell International 

Space Division 



.nterference heating effects, provides the required L/D ratio to meet 
cross range requirements, and possesses an acceptable trim range over 



i 

c 

the flight Mach number regime 



Aerodynamic design geometry of the Orbiter Veh 1C 1e is presented in Figure 
3 1-1 The Master Dimensions Specification Manual, Reference 3-2, should 
be consulted for detailed lines drawings and dimensions. A summary 
breakdown of pertinent components Is given in the ensuing paragraphs. 



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Space Division 



3.1.1 WING. The Orbiter wing was sized to provide a 171-knot touchdown 
speed (Vq) at a 15-degree angle of attack (tail scrape attitude for 
main gear strut compressed, tire flat) with body flap retracted and the 
center of gravity at the forward limit. The leading edge sweep (^5 
degrees) and aspect ratio (2.265) were selected on the basis of aero- 
thermodynami c trade studies to provide the design touchdown speed for a 
center of gravity at the forward limit with minimum wing size and to 
optimize the wing leading edge thermal protection system (TPS) for a 
reuse cycle of 100 flights prior to major rework. Spanwise twist dis- 
tribution and chordwise camber are shown on Figure 3-1 .1-1. 



3-0 



d«9«««i 



: j'KlZ-liSfi SfAMVW ML TWIST ^^:^!3;Hi!sii:.^-Tj 



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WING TWIST* AND CAMBER 



3.0-10 



SD72-SH-0O6O-1M 



0^ 



Rockwell International 

Space Division 



Control surfaces located in the wing consist of the elevons (elevator- 
ailerons) weith elevon seal (or "flipper") doors which effectively seal 
the resultant gaps when the elevons are 
deflected by fo/Zcmttipthe control surface 
leading edge. 

The wing planform reference area (2690 ft ) 
includes that portion of the basic planform 
covered by the fuselage. It does NOT in- 
clude the areas formed by wing-body fair- 
ings or areas clipped from the equivalent 
"delta" by the faired wing tips. Pertinent 
dimensional parameters are summarized in 
Table 3.1.1-1 (see also, Figures 3 - 1 - ^* — 1 
through 1.] .k-k for areas and perimeters. 

Table 3.1.1-1 WING DIMENSIONAL PARAMETERS 




PARAMETER 


SYMBOL 


VALUE 


UNITS 


AIRFOIL SECTION 

(Y o 199.0*5) 

(Y n "i63.3»0) 





0.0010 (nod) 
0012 - 6<) (mod) 


— 


OIHEDRAL (*c trailing edge] 


*., 


3.5 


dagrcai 


AREA 

Plenfor™ (total) 

Planform (exposed) 
Vetted Surface (exposed) 


5.,. 


2690 

2012.4 

1)001.2 


ft' 
ft 1 
Ft 1 


SPAN 


b w 


78.056 (936.68) 


ft ! inch) 


ASPECT *ATI0 


*w 


2.265 


... 


TAPER RATIO 


X - c e /e r 


0.20 


... 


SWEEP 

Leading Edge 

Trai 1 ing Edga 


A.. 

A„ 


»5 
-10 


degrees 
dagraai 


CHOR0 

Root (theoretical) 

Fuselage Station (0.25c) (F.S.) 

Buttock Llna (8.1.) 

Length 

Root 'exposed) 

Fuselage Station (0.25e) (F.S. ) 

Buttock Llna (B.L.) 

Length 

Tip 

Fusalaga Staclon (0.25O (F.S.) 

Buttock Lint (B.L.) 

Length 

Mean Aerodynamic 

Fuselage Station (0. 25c) (F.S. ) 

Buttock Llna (B.L.) 

Langtn 


X 



Y 



X 
9 

Y 



e r 

\ 

Y 
o 

e t 

MAC 

*0 

Y 



1008.31 

57. It* (689. 2*) 

778.5 
108.0 
80.83 (970) 

1333.30 
*68.3<t 

11. »3 (137.85) 

1136.33 
182.13 
39-56 (*7*.S!) 


inches 
Inenas 
ft (Inch) 

inches 
inenas 
ft (Inch) 

Inches 
Inenas 
ft (Inch) 

Inenas 

inches 

ft finch) 


SLOVE 
Swaap 

Thaoratlca) Intersection 
Fusalaga Station (F.S.) 

Buttock Line (B.L.) 


Aoiovi 

X 



Y 

a 


81 

102<i.O 
1S3.0 


degrees 

'nenes 
1 nches 


ELEVON (ona tlda) 

Inboard/Outboard Split (BL) 

Araa 

Span 

Aipact Ratio 

Fuselage Station (0.25c) (F.S.) 
Olstence (centrold ;o Mngellne! 


Y 


S 

< 

MAC, e. 


311 

206.57 
28.37 

4.03 
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1*09.375 
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Rockwell International 

Space Division 



3.1.2 



3.1.3 



FUSELAGE (OR BODY). The Orb iter fuselage was designed to accommodate 
a variety of payloads and house the crew and maneuvering control 
systems. Nose camber, cross section, and upward sloping forebody sides 
were selected to improve hypersonic pitch trim and directional stability 
and in conjunction with wing-body blending, to reduce entry heating on 
the body sides. Attitude Control Propulsion System (ACPS) pods have 
been incorporated with the OMS and are located in the aft body fairings. 
Hinged surfaces attached to the fuselage include the cargo bay doors 
and the body flap. The cargo bay doors have 13 hinges on each side of 
the fuselage. The six forward hinges on each side are covered with TPS 
and faired fore and aft. The aft seven hinges have no TPS and no fair- 
ings. The body flap is used to protect the Shuttle main engines (SME) 
during entry and to provide trim capability to relieve elevon loads. 
Pertinent dimensional parameters are summarized in Table 3.1.2-1. 

Tabla 3.!. 2-1 FUSELAGE 0IMEN5I0KAL PARAMETERS 



PARAMETER 


SYMBOL L 


VALUE 


UNITS 


LENGTH 








ftafaranea 


I. 


1290.3 


Inch as 


Nosa Fusalaga Station (F.S.) 


X 


238 


I nchas 


DEPTH 


". 


19.92 (239) 


ft (Inch) 


Maximum it F.S. 


X 


1280 


Incnas 


WIDTH 


"i 


22.0 (264) 


ft (inch) 


Maximum at F.S. 


X 

o 


1528.3 


i nchas 


AREA 






4 


PI an form 


s. 


1 91 *•. J. 


ft 1 


Watted Surfjca 


Sw 


563* 


ft 1 


Basa 


S, U.I 


365.7 


ft J 


QMS ?od> 


*»O0| 


71.0 


ft J 


CARGO SAY 








Diamatar 


dc. 


15 


ft 


Lanijth 


u, 


60 


ft 


GLOVE 








Fusalaga fntsnaetlon (F.S.) 


X 


500 


1 nchas 


(B.L.) 


r 


102 


Incnas 


(8a»«d on OML - TPS :nctudad) 








BODY FLAP 








Araa (planform) 


s„ 


135-75 


ft 1 


Span (aquivalant) 


».. 


2*1.33 


I nchas 






81 


Incnas 


Chord 


s «. 






Hlnga Lina (F.S.) 


1 X 
1 ° 


1532 


Inehas 



VERTICAL TAIL. The vertical tail has been sized to provide a low- 
speed C of 0.0013 at an angle of attack of 13 degrees about a center 

of gravity located at the aft limit and has a reference area of ^3.25 
ft 2 including the rudder/speed brake. The rudder is split along the 
Orbiter buttock plane to provide directional stability augmentation in 
the hypersonic/supersonic flight regimes and to apply drag modulation 
for the subsonic flight phases, approach and landing. The sect. on 
profile is a five-degree half-angle, 60 to hO percent double wedge air- 
foil. Dimensional parameters are summarized in Table 3 - 1.3-1- 



3.0-12 



SD72-SH-0060-1M 



4* 



Rockwell International 

Space Division 



Teole J. 1.3-1 



VERTICAL TAIL DIMENSIONAL PARAMETERS 
(Including rudder/speed brake) 



PARAMETER 


SYMBOL 


VALUE 


UNITS 


AIRFOIL SECTION 





10* Symmetrical 





(root-tip) 




60* - *0» double 
wedge 




AREA 


S» 


"113.25 


ft ! 


SPAN 


b. 


26.31 (315.72) 


ft (inch) 


ASPECT RATIO 


m 


1.675 





TAPER RATIO 


K • c t /e r 


O.*0* 


— 


SWEEP 








Leading Edge 


*•.. 


*5 


degree! 


Trai 1 Ing Edge 


*-.. 


26.2 


degree! 


CHORD 








Root 


C 


22.37 (268.5) 


ft (incn) 


Tip 


c c 


9.5* (108.*7! 


ft (inch) 


Mean Aerodynamic 


3, 


16.65 (199-31) 


ft (Inch) 


Fuselage Station (0.25O F.S. 


J 


1*63-35 


incn 


vaterllne w.L. 


I 
o 


635.5 


Inch 


RUDDER/SPEED BRAKE 








AREA 
SPAN 


5 

b 


97.8* 

16.55 (198.60 


ft 2 

ft (inert) 


CHORD 








Mean Aerodynamic 


c" 


6.07 (72.3*) 


ft (Incn) 


Fuselage Station (0.25c) F.S. 


X 




1575-77 


incn 


Watarllne W.l. 


'• 


670. *1 


in* 



3.I.I4 TOTAL VEHICLE. Cross sectional data defining the total Orbiter 
Vehicle geometry are presented in Figures 3 - 1 - ** — 1 through 3.].k-b. 
These figures provide the cross sectional area variation for components 
and total vehicle and the perimeter distribution for components and 
total vehicle. Total vehicle dimensional parameters are summarized in 
Table 3- 1 .*»-1- 



Taole J.l-*-l 



TOTAL VEHICE SImEnSIChAl PARAMETERS 
(fuselage plus exposed wing) 



"ARAMCTER 


SYMBOL 


VALUE 


UNITS 


AREA 








PI an form 


'TO»*i 


3952 


ft J 


Wetted Surface 


^"TOfl 


11.136 


ft 1 


LEN5TH 








Overall 


L 


122.0 (1*6*) 


ft (incn) 


Reference 


L. 


107.5 (1290.3) 


ft (inch) 


SPAN 


»w 


78.356 (936.63) 


ft (incn; 


ME15HT 








Bear- Up 


gi*» y» 


*6. 1* (553-68) 


ft (Incrj 


tear-Down (static position) 


"fliltom 


53.76 (6*5.12) 


ft inch! 



3.0-13 



SD72-SH-0060- 



'1* 



Space Division 

Rockwell International 







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Space Division 







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Rockwell International 













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3.0-17 



SD72-SH-0060- 1M 



'i* 



Rockwell International 

Space Division 



3.2 REFERENCE AXES AND SIGN CONVENTION 

Reference axes and sign conventions are consistent with those for con- 
ventional aircraft. The Orbiter Vehicle axis system for vehicle design 



drawings and mass proper* 
ties statements is illus- 
trated in the sketch. 
This axis system is de- 
fined in the Space 
Shuttle Master Dimensions 
Specification, Reference 
3-2, and on Figure 3.1-1. 
All vehicle design drawing 
axes systems are in 
accordance with NASA Phase 
B Technical Directives 
2519 and 2519A. 



uaoramiiii 




m tis 

( or P»TLOU) 
BAT 



Actual diitanc* 
ii *3f'««h*i. 

C«rr«ct dtm«nit«A for 
r«f«r«ncc body l-fta.'** 
il 231 inchai 



3.2.1 AERODYNAMIC REFERENCE AXIS SYSTEMS. Definitions of the Orbiter 

Vehicle aerodynamic reference axis systems are illustrated in Figure 
3.2.1-1. The posi tive X-axis for the Orbiter body axis system is 
shown parallel to the Fuselage Reference Line (FRL) . Si gn .convent ions 
for forces, moments, veloci ties ,. and accelerations ar.e also shown on 
the figure. The aerodynamic reference axis systems are sets of con- 
ventional, right-hand, orthogonal axes with the X- and Z-axes in the 
plane of symmetry and with the positive X-axis directed out the nose 
(in the body axis system) or pointing into the component of the wind 
(in the stability axis system) which lies in the plane of symmetry. 




[tar** I V'^rA : k 

A l ^V (*•) STAIUL.-TY AX I." 5Y1T;w 

(•) BODY AXIS SYSTEM 




S 



ORBITER REFERENCE AXIS "-YSTE 



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3 . - '. 8 



SD72-SH-0060- IM 




Rockwell International 
Space Division 



3.2.2 AERODYNAMIC SIGN CONVENTION. Sign conventions for the aerodynamic 
force and moment coefficients used in this report are illustrated in 
Figure 3.2.2-1 for the stability axis system. Directions on the figure 
are positive as shown. 



| Stability A\t!| 





Figure 



ORBITER SIGN CONVENTION 




j&y 



3.0-19 



SD72-SH-0060-1M 



'1* 



Rockwell International 

Space Division 



3.3 AERODYNAMIC CONTROL 

Orbiter Vehicle aerodynamic control surface deflections, forces, and 
hinge moments are summarized and illustrated in the sketch. In general, 
control surface deflec- 
tion angles are measured 
in a plane perpendicular 
to the control surface 
hinge axis. An excep- 
tion is the rudder/speed 
brake control surface (s) 
deflections which are 
measured in a plane 
parallel to the fuselage 
reference plane (FRP) . 
Each aerodynamic control 
surface and deflection 
is discussed separately 
In the ensuing paragraphs 
of this section. 

3.3.1 ELEVONS. The elevons 
are divided into four 
segments, right- and 
left-inboard and right- 
and lef t-outboard. 
Gaps between the fuse- 
lage and elevon and 
between the inboard 
segments to which the 
data herein are appl i - 
cable are those base- 
lined in MCR 0315. A typicaT elevon control installation is shown in 
Figure 3-3.1-1 . 




reiitlr* 
Dsfltction of 


An|U 


Atro Forces 
ind Mo««ntl 


Hlii|* 
Hoatnt 


ljuddtr, lr 


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•Cy • •<:, 


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♦* 


♦c. 




lody Fl.p, »»f 


•• . -» 


-=» 


"Chbf 



Tobl.3.3rl MAXIMUM CONTBOl SU6FACE EEflECTIONS AND RATES 



CONTROL SURFACE 

1 


DlflECTION 

SYMlOI. 


DISPLACEMENT 
'MAXIMUM' 


RATE 
normal OPERATION 


d»g'»»i 


d«g/l,c 


ElEVONS 

Eicvd'or 

AiI«ron 








-35 TE UP 

♦ 20 T E DOWN 


20 
20 












-j 








\ 


[-j 






[-«*_-»* 6,0* .120* 


RUDOER 


«, 


:22.8 


!0 


5MF.D8RAKE 


5,. 


1, S7.2 


5 


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«,. 




-u. y T6 UP 

+ 22.55 TE OOwn 


1.3 



3 .0-20 



SD72-SH-0060-1M 



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Rockwell International 
Space Division 




OCJC1 

OCZDCZ7 



TYP CROSS SECTION 
(INBOARD I OUTBOARD) 



tUYW tUVKl 



f.,-.. 3 3 11 

IllVON CONTROL | 



3.3.2 



The surfaces are servo-actuated with four actuators to control the four 
segments. These surfaces are employed for pitch and roll, control and 
pitch and roll trim. Maximum control surface deflections and rates are 
given in Table 3.3-1. The elevon deflection range is "35 degrees 
(trailing edge up) to +20 degrees (trailing edge down) except during 
entry where it is limited to +10 degrees to prevent excessive heating. 
The aileron function deflections are shown on the table. 

RUDDER/SPEED BRAKE. Directional control of the Orbiter is achieved 
aerodynamical ly by means of the rudder. During entry, at high angles 
of attack, the rudder is augmented by RCS (see section 3*6). The 
rudder is split into four panels, two per side (upper and lower), which 
are deflected together for yaw control and deployed symmetrically, in 
opposition, for drag modulation (speed brake function). Each pair 
(upper and lower) of panels is actuated by power hinges driven by a 
common torque shaft as illustrated in Figure 3.3.2-1. 



3 .0-2 1 



SD72-SH-0060- 1M 



0fc 



Rockwell International 

Space Division 



( »im 



mtn/ut vm 




•IK ua [iit) 



in war >avt**u 
■IK mi (IW| 



• l *•«*■ Mivt tjniT |*v) 
•M (Mitel uaiT fu twMM 
Ml [WW. WIT •« I'll! MUU 

I "hawk mt—t uu uar hit 

< Hafll Minn ■• UK (IUCT1M 

i« i**Miri 

•iucTi«m rw mu tiMi 



»'••<• 3.3 2 I | 

RUDDER SPEEDBRAKE CONTROll 



Rudder/speed brake deflections are given in Figure 3-3.2-2 and in 
Table 3-3-1. 



5 r ~KU0DEI DETLBCTION 

5 - SPEEDBAAKE DtriJCCTION 

D.tlrctio"* ihu«R flflllil to 
(»••!»(• r«f«r«nc* plana 

5 =2**ctan[cosA tan5 s , ] 




5 r 



DEGREES 
10 



A= ANGLE OF * TO Z-IODY AXIS 

r 3«..33I3.° 
S' r HALF ANOIE OF SPEEDHAKE 
M DEFLECTION MEaSUHEDIN 

n*NENO«MAt TO V 
f l yPDti: AWP IPEEPgHAKE PEfXtCTiOg 




.-•6; *J-r i 




5 f •11.21— 



"*r 



i ■ ' ■ ■ * >- A 



to 



g -DEGHEES 



COMBINED KUDD ER/S PEEDBH*iq t MAXIMUM 
DEFLECTIONS 



Wtl 



n.xrt 3.3.2-2 j 

ORIITEft RUOOIR/SPUDBRAKE 



3.0-22 



SD72-SH-0060-1M 



#JI 



Rockwell International 

Space Division 



3.3.3 BODY FLAP. Trim capability to relieve elevon loads is obtained by 

body flap deflection actuated by power hinges as shown in Figure 3-3.3-1 



~\ 




nci ni<i unit owe wow)] 
* ■■' ■ \ 




etf^^'S^ 



[BODY 



,,..t 3 3 3 1 ■ 

FLAP CONTROL 



Body flap deflection is from -11.7 degrees (trail ing .edge up) for entry 
with a forward center of gravity to +16.3 degrees (trailing edge down) 
for entry with an aft center of gravity. Maximum positive body flap 
deflection is +22.55 degrees as shown in Figure 3.3-3-2. 



H. 




0* 


- 6.3' 


-11.7* 


-IS* 


.16.3* 


• 10' 


• J2.55" 


• l«.25* 







!,"• 3 3 3 J 

iODY FLAP DCFLKTJON 



3 .0-23 



S D 7 2 - S H - 5 



'1* 



Rockwell International 

Space Division 



3.4 LANDING GEAR AND GROUND CLEARANCE. The Orbiter Vehicle landing gear con- 
sists of a double-wheel steerable nose gear and two, double-wheel, wing- 
mounted, main gear. The gear is designed for a maximum landing weight of 
227,000 pounds and a maximum landing velocity of 221 knots. Maximum 
allowable sink rate for the Orbiter Vehicle with a 65,000-pound payload 
is 6.0 fps. Gear deployment velocity is 300 knots maximum. Steering 
capability Is ±10 degrees and the crosswind constraint is 20 knots maxi- 
mum. The landing gear installation is illustrated in Figure 3.4-1. 

Ground effect, as shown in the data sections of this report, is given as 
a function of the ratio of height-above-ground to wing span. The height- 
above-ground is measured to a point on - the vehicle just aft of the trail- 
ing edge of the inboard section of the elevon (FS 1506.84, WL 282.71). 
Height-above-ground as a function of angle of attack is given in Figure 
3.4-2 for various values of the ratio h/b. 

The touchdown attitude is restricted by the ground scrape angle (a s ) as 
illustrated on Figure 3.4-2. Scrape angle(s) Is given for three landing 
gear strut conditions: fully extended; static; and fully compressed-tires flat 
when the body flap is in the landing position (-11.7 degrees). The effect 
of elevon deflection (trailing edge down) is to further restrict the 
touchdown attitude as shown on the figure. 




3.0-24 



SD72-SH-0060-IM 



0£ 



Space Division 

Rockwell International 




~- — *•*#»•*<• Point For n 

_, „, *„ 1506.84 

"s , «EF Z 282 71 

_J 1- .._ - GHOUND UNE 

SSf ALSO HGUȣ 3.1 -1 INSEt] 



b w = 78.056 fl 



feet 




4 8 \l 16 

ANGLE OF ATTACK a ~ Degrees 

->m- EtEVON SCRAPE 



BODY flA P SCRAPE -* / 

2Q | — f- 



a 10 

SCtAPE 

Degrees 




5, F =-11.7= 

LANDING 



_L 



X. 



_L 



4 8 12. 16 

ELEVON DEFLECTION 8 e ~ Degrees 



Landing 
Gear 
Strut 

EXTENDED 

STATIC 
COMPRESSED 



GROUND CLEARANCE 



3 .0-25 




Rockwell International 

Space Division 



3-5 



THERMAL PROTECTION SYSTEM. The Thermal Protection Subsystem (TPS) is 
designed to protect the primary airframe structure from the effects of 
aerodynamic heating during ascent and entry. In general, the TPS consists 
of reusable surface Insulation (RSI) 'tiles' of three types having a 100- 
mlssion capability. The three types of insulation used are: 

FRSI (flexible RS I ) to 700°F (entry) and 750°F (ascent) 
LRSI (low temperature RSI) 700°F to 1200 C F (nominal) 
HRSI (high temperature RSI) 1200°F to 2300°F (nominal) 

The TPS is required to provide adequate capability for assuring safe earth 
return and intact landing of the Orbiter Vehicle following abort-once- 
around(AOA) and return-to-1 aunch-s i te (RTLS) abort. General area TPS in- 
stallation is shown in Figure 3.5-1- 



f„..d S.lno In 



STRUCTUkt 




ncr 

tsodii'fl Edg« 



• THERMAL PROTECTION SYSTEM 

Rbl RfUSABlE SURfACE INSUtATION 

• f RSI HIT |Noma.| 

• H RSI MlGM TEMPERATURE 

• I RSl ■ IOW TEMPERATURE 

• RlC RElNfORCED CARBON CARBON 



ORBITER 



i 3 b-l 

VEHICLE 



102 



anH .,.„- influence the aerodynamic characteristics (particularly 

&™£v$z sisr-r.-s'isiTii «='sm; 

can be found in Reference 3-3- 



3.0-26 



SD72-SH-0060-1M 



0^ 



Rockwell International 

Space Division 



X,105 




MAXIMUM 
AUOWASIE STEPS 



^ 



////\ *°- 04< " 1 



; Xo'i'» 



rOIWAbO FACING 



VU.I 






**r f*c«wc 
i oownstiiami 
-O.OSO.m. 





GAP Ik. fin II«'!IMJII 

COATING j lOW riMPiiATuai 



MAXIMUM AttOWAILE GAP 

lowvr Surfoc* 0.045 t O.MQ lnch«i 
Upp-x Suifoc* 0.055 i 0.020 Inch.. 
TPS Gap Edge Rodiu* 0.060 Inch** IMonmum) 



/C 



5UBFACE WAVINESS CRITERIA 
I Mam mo in Wovinti* 



W 



H/t =0 0015 
H/l 



= 0025 



to««i W.i>g(E»c»pl EUvonl 
low.. Fv,.lo 8 . X/L< 0.3 
lawir Eui«lag« X/l>0.3 
Upp«f Fui<lo|)>, Uppar Wiflf, 
El.yoni, Vaflical Toil 



3 »-17 



G 



ORBITER MOLD UNE/STEP CRITERIA 



3-6 



an «ui» 



REACTION CONTROL SYSTEM. Attitude control of the Orbi ter during entry 
f. provided by the aft reaction control system (RCS) in roll and p. ten 
up to dynamic pressure 
levels of 10 and 20 psf, 
respectively. The RCS 

thrusters are located In /C^^S^ ^-S^^^V^"^^' ^-^^Si-TilT 

the OMS pods as shown in 

the sketch. For dynamic 

pressure levels exceed- 
ing 20 psf, sufficient 

elevon (elevator-aileron) 

control authority is 

avai lable and the roll 

and pitch thrusters are 

deactivated. The 

blanketing effect of the 

wing at high angles of 

attack necessitates the use of yaw thrusters to augment the rudder control 

until the angle of attack is reduced to approxi- 
mately ten degrees. Aft RCS jet/aerodynamic in- 
teraction, illustrated in the sketch at left, is 
discussed in appendix B and data are presented 
in Section b.O (where applicable). 





3.0-27 



■ r>77- £ ;w-(>nfiri-iM 



0$ 



Rockwell International 

Space Division 



3.7 AIR DATA SYSTEM. The air data system (ADS) is designed to provide air 

data relative to the vehicle at altitudes where winds, in conjunction with 
vehicle speeds, can produce relatively large errors in inertially derived 
air data. At approximately 100,000 feet of altitude (M « 3-5) two air 
data probes are extended from the Orbiter forebody (FS 299, WP 324) to 
sense vehicle flight conditions. One probe is located on each side of the 
orbiter forebody canted 10 degrees, nosedown, relative to the FRL. The 
ADS probe is illustrated in Figure 3 • 7 — 1 - The air data probe is instru- 
mented to measure total temperature (T T ) , local static pressure (P 4 ) , and 
angle of attack from three pressure ports (P l , P 2 , and P T ). 




MEASUREMENTS 

Tooiporoturt T. 

Local Static Prvittfr* ■, 

Anglo al Attack 'i.'i,'- 

Mach Numbar - I { P, , •, ) 
Spoad of Sound = f(T,,M)-^f(T.) 
V.lociiy = Mo 

All.t.do = I ( \ ) 



NOTE FVob.i caniod 10' 

HMO down ralolivoto FRL 



Al« DATA nOIC 12 SIDES] 
FS jot. 16 
Wl J21.5JO 
II iJ3305 



i-i-tt 



AIR 



Fiavro 3.7-1 

DATA SYSTEM PROBEJ 



3.8 CREW ESCAPE SYSTEM. The Crew Escape System (CES) is designed to provide 
safe egress and recovery for two crewmen to a maximum altitude of 75,000 
feet. A sketch of the CES is given in Figure 3.8-1 which also provides 
the aerodynamic sign convention for the man/seat configuration. Free-air 
and proximity aerodynamic data for use in simulation studies of man/seat 
motion following ejection are provided in Section k.3. 

Components integral to the CES are two rocket-powered ejection seats 
mounted side-by-side and' two ejection panels integral with the overhead 
structure. The ejection seats have powered, integrated, torso restraint 
harness systems utilizing single release controls with stabilization drogue 
parachute systems. The overhead ejection panels are equipped with a pyro- 
technic train for severing the inner and outer cre,w module structure and 
the outer structure of the forward fuselage to provide an unobstructed 
path for the man/seat. The hatches are also equipped with thrusters and 
hinges necessary to propel the hatches clear of the man/seat trajectory. 
OV102 also includes a ballistic guillotine for severing overhead displays 
and controls electrical cable. 

3.0-28 



SD72-SH-0060- 1M 



'i* 



Rockwell International 

Space Division 



S RE = 5.945 ft 
L REF = 2.76 ft 




(SEAT REFERENCE POINT] 



-SEAT CLEARANCE 
/_, ^^L / , -ESCAPE HATCH 



-EJECTION 
RAIL 



94' M J? 

6-15-77 



Figure 3.8-1 

CREW ESCAPE SYSTEM 



3 .0-29 



SD72-SH-0060-1M 



^ 



Rockwell International 

Space Division 



3.9 SHUTTLE INFRARED LEES IDE TEMPERATURE SENSING 
side Temperature Sensing (SILTS) experiment 
tailed temperature maps of the Orbiter Vehic 
surface for the entire entry heating period 
In the SILTS fin tip assembly which replaces 
tip. The forward portion fs a hemispherical 
pane windows for viewing forward and to the 
The dome contains window covers and a window 
terior surface of the SILTS fin tip is cover 
usable surface Insulation (HRSl) tiles. Dur 
positioned alternately at the two windows at 
objective of the experiment is to identify 
weight might be realized. Figure 3-9-1 pres 
experiment. 



The Shuttle Infrared Lee- 
is designed to obtain de- 
le wing and fuselage upper 
The experiment is located 

the baseline Orbiter fin 

dome containing two double- 
1 ift-side of the Orbiter. 

cooling system. The ex- 
ed with high-temperature re- 
ing entry the IR camera is 

seven-second intervals. The 
areas where reductions in TPS 
ents a sketch of the 




figort 3.9-1 



SILTS EXPERIMENT 



,10 MASS PROPERTIES. Mass properties data for the Orbiter Vehicle should be 
obtained from current Space Shuttle Mass Properties Status Reports for 
the Orbiter Vehicle. These status reports are Rockwell International, 
Space Division reports and are published monthly (e.g., see Reference 
3-4). 



3.0-30 



SD72-SH-0060-1M 



#1% 



Rockwell International 

Space Division 



3.11 SURFACE DESIGN REQUIREMENTS. The aerodynamic integrity of the Oruiter 
Vehicle Is dependent on the efficiency of all surfaces exposed to the 
air flow such that surface design requirements are critical to the defi- 
nition of the vehicle aerodynamic characteristics. The allowable aero- 
dynamic surface alignments, Outer Mold Line (OML) fairing and smooth- 
ness requirements, and the sealing requirements which established devia- 
tions affecting both aerodynamic and aerothermodynamic characteristics 
of the Orbiter Vehicle are discussed i n th Is subsection. 

Aerodynamic surface alignments are outlined below. 



WINS INCIDENCE TOLERANCE 



807 



X-Z P1AN F AT WING FUSELAGE JUNCTURE 

TTHB 

DESIGN INCIDENCE; 

ACTUAL INCIDENCE 




A-B * a Z5 INCH 



CRITERIA 



RATIONALE, 



• MAXIMUM ALLOWABLE WING INCIDENCE TOLERANCE 
AT WING-FUSELAGE JUNCTURE FOR THE LEADING 
EDGE ELEMENT RELATIVE TO THE TRAILING 
EDGE ELEMENT (FUSELAGE AND WING SUPPORTED 
IN MATING TOOLING I 



.a 25 INCH 



MAINTAIN AC- 
CEPTABLE IM- 
PACT ON ELEVON 
REQUIREMENTS* 
DUE TO STRUCT. 
MISALIGNMENTS 



WING DIFFERENTIAL INCIDENCE TOLERANCE 



X-? PLANE AT W INC, FUSELAGE JUNCTURE , Y Q 
-LEFT WING PANEL 
. RIGHT WING PANEL 



RATIONALE 



• 105 




• MAX ALLOWABLE DIFFERENTIAL INCIDENCE 
BETWEEN THE LEFT AND RIGHT WING 
PANELS AT THE WING-FUSELAGE 
JUNCTURE (VEHICLE SUPPORTED IN 
TOOLING JIG) 



CRITERIA 

«a 375 INCH FOR THE 
LEADING EDGE ELEMENT 
OF ONE PANEL RELA- 
TIVE TO THE TRAILING 
EDGE ELEMENT FOR THE 
OTHER PANEL 



MINIMIZE DEGRADA- 
TION OF AILERON 
EFFECTIVENESS DUE 
TO STRUCTURAL 
MISALIGNMENT 



WING'S DIFFERENTIAL INCIDENCE TOLERANCE EQUALS LEFT WING'S 
INCIDENCE TOLERANCE MINUS RIGHT WING'S INCIDENCE 
TOLERANCE OR, 

C * ^'^IeFTWING ~ lA ~ 8) RIGHT WING 



3 .0-3 1 



SD72-SH-O06G- IK 



#jl 



Rockwell International 

Space Division 



DIFFERENTIAL DEFLECTION OF WING TIPS 

ft 




B < 1.0 Inch 



MAXIMUM DIFFERENTIAL DEFLECTION 
OF WING TIPS (FUSELAGE AND WING 
SUPPORTED IN MATING TOOLING) 



RATIONALE: MINIMIZE 
ASYMMETRIC LIFT & ROLL 



MAXIMUM ALLOWABLE TWIST TOLERANCE 




CHORD ACTUAL 
LOCATION 




r\h 



TWIST 



A ■ CHORD'S ACTUAL TWIST. 
INCHES 

L. FEET I • CHORD'S DESIGN LENGTH, 



/JS1 m 

A,INCHES»| |*_\ — CHORD DESIGN LOCATION 
LIFTING SURFACE TWIST TOLERANCE •■£-, INCHES/FOOT 

CRITERIA 



• MAXIMUM ALLOWABLE TWIST TOLERANCE FOR < 0.005 INCH 

ANY LIFTING SURFACE (WING OR TAILI PER FOOT 
(VEHICLE IN TOOLING JIG) 

• THE MAXIMUM ALLOWABLE DIFFERENTIAL 1*0.005 INCH 

TWIST TOLERANCE PER 12 INCH SPANWISE PER FOOT 
DISTANCE (VEHICLE IN TOOLING JIG) 



RATIONALE 

MAINTAIN SURFACE AERO 
EFFICIENCY AND REDUCE 
CONTROL REQUIREMENTS 



3.0-32 



SD72-SH-0060- 1M 



to 



Rockwell International 

Space Division 



ERROR IN LOCATION OF LEADING AND TRAILING EDGES 

ERROR IN LOCATION Of LEADING AND TRAILING theoneticai tmiiing 



EDGES 
CRITERIA 

• ACTUAL L E ELEMENT 

SHOULD LIE WITHIN 
AN a 06 INCH-RADIUS 
CYLINDER FROM THE 
DESIGN LEADING EDGE 
ELEMENT 

• ACTUAL T. E. SHOULD 

LIE WITHIN a06 
INCH-RADIUS CYLIN- 
DER FROM THE 
THEORETICAL TRAIL- 
ING EDGE 

• REQUIREMENTS CHECKED 

AFTER LEADING AND 
TRAILING EDGE ASSEM- 
BLIES HAVE BEEN FUUY 
FASTENED TO CENTER. 
SECTION OF THE SURFACE. 



EXE CtEHEIT 



RATIONALE 



PROVIDE ACCEPTABLE 
AERO CHARACTERISTICS 
WITHOUT IMPACTING ,.. M ,« 
WEIGHT AND COST 




t 



THCOHETICAl 
IEMING EDW 
ElEKEXT 



p, • IOUT10N Of » POINT ON ACTUW. LEADINt EDCt EIDWT 
0, • LOCATION OF * POINT ON ACTWl TNAILINS EKI B.EXf.lfT 
r, • DEVIATION ENKON OF p, IN INCHES 
r, ■ DEVIATION EKWN OF Pj IN INCHES 
I ■ MAUN* M.LOWW.E DEVIATION ENNON 



VERTICAL TAIL CANT AND INCIDENCE TOLERANCE 




PERPENDICULAR TO WATER PLANE * 

A,INCHES- 



____mi 



CANT TOLERANCE - -f- . INCHES/FOOT 
INC IDENCE TOLERANCE -4-. INCHES/FOOT 




L, FEET 



CRITERIA 



RATIONALE 



• MAXIMUM ALLOWABLE VERTICAL TAIL CANT 

(VEHICLE IN TOOLING JIG) 

• MAXIMUM ALLOWABLE INCIDENCE TOLERANCE 

OF THE VERTICAL TAIL (VEHICLE 
IN TOOLING JIG) 



10.025 INCH MAINTAIN VERTICAL 

PER FOOT TAIL AERO EFFICIENCY 

„„,i,^u ANO REDUCE CONTROL 

1 iro bvtT REQUIREMENTS 
per root 



The aerothermodynamic criteria pertaining to surface discontinuities and 
waviness are based on aerodynamic efficiency requ. rernents of _ 1 i ft.ng 
surfaces and the prevention of premature trans. t.on from laminar to tur- 
bulent boundary layers during the high heating portion of '"try. The 
prevention of premature separation of the boundary layer on all fixed 
and movable lifting surfaces is also important. Aerodynamic «^«c^y 
is affected to a much greater extent by surface cond.tions over forward 
regions of components rather than aft regions. Tolerance criteria are, 
therefore, generally more severe for forward sections of the vehicle 
surfaces and are somewhat relaxed for aft portions. 



3.0-33 



SD72-SH-0060-1M 



* 



Rockwell International 

Space Division 



Surface discontinuities consist of steps and gaps. A step is an abrupt 
deviation from the faired contour; e.g., a lap joint ( fcmilZi 1 1 '4 ) . The 
tolerance for a forward facing step is generally the same as for a rear- 
ward facing step unless specifically noted otherwise. The step require- 
ments (cf. Figure 3-5-2) apply to all surface irregularities which have 
a dimension normal to the OML except RCC areas. RCC step and gap cri- 
teria are shown below based on trajectory 2689. 

B*SB)« mECiCW 2688 



*«- 
















\ 

































wo toe 

ENTW TTHE - SEE. 

ta/ta. STEP CRITERIA 



14 


\ 










11 - p 


1 


\ 




























M 













Ma loo iooo 

dim Tilt - SEC. 

RCOTCC G*> CRITERIA 



A gap is defined as an abrupt negative deviation from a faired contour 
followed by an abrupt positive deviation such as is caused by a poorly 
matched butt joint (0 = 5S SS SF 2 ') or spaces between TPS tiles. TPS gap 
criteria are outlined below and apply to all surface gaps with the ex- 
ception of RCC areas (given above) and control surface gaps. Gaps shall 
not allow any increase In air leakage. 



TPS W CRITERIA <PR--FU3fT) 

BASIC KDUIfBOTi NIHimZE GAP WIDTH AT THE ASUMWUC SURFACE 

o LOO SURFACE: 0.0*6 *0.CE0 1H0€S 

<HEUJ» A LDE: ^, ■ Z3B, ^ • 53B TO ^-SB, ^-20 

AW x^ SB, Z • 20; L0£R SURFACE CF WING; 
GICVE L.E. TO LRSI; LITER AW LOG BCDY FLAP; 
BASE I€AT SHIELD) 
o UPPER StfFACES: O.CEStO.OZ) INOC (ALL SURFACES MOT D3TJG1 ATOB 

TILE PATTEJKD SO THAT NO GAPS ARE AUGfO WITH LOCAL SURFACE STOfUIG DURIN3 
BflRY 

IPS MP EDGE MILS: 0.0E INCHES OWIHW 
3.0-34 



SD72-SH-0060-1M 



JQI 



Rockwell International 

Space Division 



A wave is defined as a smooth variation from a faired contour. The wave 
height (H) is the distance measured normal to the surface between a low 
point on the surface and an adjacent high point. The wavelength (21) is 
twice the distance from a low point on the surface to an adjacent high 
point. (Refer to Figure 3.5-2 for maximum allowable gaps and surface 
waviness criteria.) The waviness requirement applies to all external 
surfaces. 

The master lines OML fairing requirements permit no reflex fairing on 
lower surfaces. Reflex fairing is permitted on upper surfaces. Con- 
tinuous second derivatives of equations defining the surface of the _ 
lower forward fuselage are required. The maximum manufacturing fairing 
deviation from the theoretical fairing is ±0.06 inch consistent w. th the 
OML smoothness requirements, TPS thickness requirements, and aerodynamic 
surface alignment requirements.^ Maximum surface irregularities, includ- 
ing RMS surface finish, are defined below. 

HI0€ SJFACE FINISH CRITERIA DURING EXTW 



o jmJES TO ALL EX1EJJW. SJWCES CJ5I, U5I, RBI, RCC. AND ICTALUC TP5) 

o DEFINITION IF mVW ALUXA3LE 3WLL SCA£ I&EGIUMTIB 

• o 3D0yM IK. IK SURE FINISH 

O.0B2 IN. JWUTIDE 3W1 SO£ WVINESS (IN ANY DIKTIOO 




o ptotibewne o.om m 

o HOLES, SOKTOE, OWS 0.0GB IN. WIDTH 
0.005 IN. CEPTH 




Penetration criteria during entry are outlined below. 



KSE LANDING i£AR DOOR 01 

o STEPS - 1 0.C07 M. WON* *» DlfECTTCN 



o 







uwmowi ws - o.c» b. win * o.n W. EP 
cr eojivalent area, at sap per door interface 

TM(SVBS5*S-0.0«t0XaDIN. oniLED WITH H1W PIBStt 
aWIENT TH3m. BARRIER) 



RAMI EXIEWL V*. ATTAMCNT M. 



o STEPS - t 0.017 B. fWXDW 

6W5 - 0.CB0 W. HKW OASED CN 5.0 IN. >WDW CIRCLE DW€TER> 



3.0-35 

SD72-SH-0060-1M 



* 



Rockwell International 
Space Division 



Surface Irregularities due to protuberances such as air data probes, um- 
bilical attachment, vents, and nozzle ports must be assessed on an In- 
dividual basis. Such Items are shown on Figure 3.11-1 and are assessed 
in Section *♦.! (Table <t.l-l). 



CARGO wr 


BOWS — 


i 










■ SAPS 




\ 










- HINGE COVERS 








HA IN PROPULSION AND 












OMS NOZZLES 


RECESSCO thermal CLASS - 






<*. 










• WNOSHIELO i 












-^Tu 




- OBSERVATION WINDOWS^ 
















- HITCH UIN00W5 // 










if 




"~-— T-0 UW1LICAL 








iCs*i^r 




^A^3SC 








s^y**' 


4T0^*j/ 




/ <^; 




ICS NOZZLE -v AL, 


r^-^J ' ' : 


1 


/ ' ' - 




CAVITIES \V/^^^^ 




I 


ELEVONS 


^— FLIPPER OOORS 

■ TMIL1N4 EDGE STEPS 






»EHTS 
- CARGO 8AT 
■ FORWARD RCS 




• SPANHISE 

- 511-INCH 


SAPS 
SAPS 


i- AIR OATA PR01E5 




■ CABIN 

- OMS »CS 

- ArT FUSELAGE 




(INCLUDES AIL OTHER RKOTUICRAIICES HOT 
IDENTIFIED AWVE) 






Figure 3,11-1 












PtOTUBEHAMCt ITEMS REQUIRING SPECIAL TREATMENT 1 



The prevention of unprogrammed air leakage from inside the Orbiter or 
through lifting surfaces is Important in maintaining lift effectiveness 
and minimum total drag. An unsealed surface has more profile drag and 
drag-due-to-lift than a sealed surface. 

OUTER MOLD LINE SEALING REQUIREMENTS DURING ENTRY 

. TPS ACREAGE 

. SEALED (SEALING BENEATH RSI IS ACCEPTABLE FOR LOW PRESSURE GRADIENT REGIONS. 
HIGH SURFACE PRESSURE GRADIENT REGIONS REQUIRE OML THERMAL 8ARRIER5) 

. TPS ACREAGE PENETRATION INTERFACES (ACCESS PANELS, DOORS, HATCHES, VENTS, WINDOWS, 
MODULES. THRUSTERS. DUMPS, AND DRAINS I 

• tt 003 IN^IN OF INTERFACE MAXIMUM INTO COMPARTMENTS (NO CONCENTRATED HOLES 

ALLOWED) 
. RCC/HRSI INTERFACES - WING LEADING EDGE AND ORBITER NOSE 

• LOWER SURFACE SEALED WITH THERMAL BARRIER (EQUIVALENT LEAK AREA a 010 IN 2 / IN 

SPAN. REQUIREMENT FOR RCC ATTACHMENT AREAS TBDI 

• UPPER SURFACE AREA TO BE LESS THAN a 065 IN Z /IN AND GREATER THAN a 035 IN^/IN. 

. RCC/RCC INTERFACES 

. LOWER SURFACE - NO INTENTIONAL LEAKS (OVERLAPPING EXPANSION JOINTS ALLOWED) 

• UPPER SURFACE - a 015 IN 2 /IN MAXIMUM, a 013 IN 2 /IN MINIMUM VENT GAPS 
. RSI TPS GAPS MUST BE FILLED IN ALL HIGH SURFACE PRESSURE GRADIENT REGIONS 

Pi«IA» CH1K WING GLOVE VERTICAL STABILIZER LEADING EDGE. WINDOW FRAMES. 
' *! tKg EDGES *V£tm COVE. VERTICAL TAIL/RUDDER COVE. BODY FLAP 

COVE, ETC. 



3.0-36 



SD72-SH-0060-1M 



MS Rockwell International. 

Space Division 



CONTROL SURFACE SEALING REQUIREMENTS DURING ASCENT AND ENTRY (ORBITER 
102 AND SUBS) 



SEAL LOCATION 


KSIgnreqU 


ttM&ff 


IN*/IN SPAN MAX 


IN^IN SPAN MIK 


• WING/ELEVON 






• LOWER SURFACE AND END SEALS 


Q 003 (TOTAL COVE 
LEAK) 





■ UPPER SURFACE 






• RIPPER DOOR FORWARD SEAL 


0.003 





• RIPPER DOOR TOTAL EQUIVA- 


0.003 





LENT LEAKAGE AREA (INCLUDES 






TRAILING EDGE, PANEL TO 






PANEL, ETC. 






. BODY FLAP 






. LOWER SURFACE AND END SEALS 


a 003 




• UPPER SURFACE 


as AND 3.0 INCH MINI- 
MUM COVE OVERLAP 


038 


■ VERTICAL STABILIZER/RUDDER/SPEED BRAKE 






• VERTICAL STAB. /RUDDER 


003 





■ SPIED BRAKES PEED BRAKE CLOSED 






POSITION) 






• TRAILING EDGE - TtCRMAL 

■ ABB IFB 


0.003 





BARRIER 
• STREAMWISE EDGES 


REQUIRE PRESSURE SEAL 


REQUIRE PRES- 


______ —— — 




SURE SEAL | 



3.0-37 



SD72-SH-0060-1M 




#jl 



Rockwell International 
Space Division 



k.O AERODYNAMIC DATA 

This section contains the Orbl ter. Vehicle Aerodynamic data to be used 
for entry trajectory analyses, subsystem design and analyses, flight 
control analyses, and manned simulation studies. The data presented 
herein represent the best available predictions of the full-scale 
flight characteristics of the Orbiter Vehicle. 

The aerodynamic characteristics are presented in a form which will 
allow a build-up to any desired configuration and/or fl.ght condition 
by incremental addition to the bas ic coef f i cient. Longitudinal _ 
characteristics are presented for both body-axis and stabi 1 i ty-ax i s 
systems. Lateral -di rectional characteristics are presented in the 
body-axis system only. Aeroelastic data, assuming a quasi-static 
vehicle, and the effects of hypersonic and high altitude are also 
provided. Prescribed use of the data is to begin with the altitude 
table (or convert to the viscous parameter, VA) down to 300,000 feet 
(V 1 - 08) use viscous parameter tables to a value of 0.005, and 
transition to the Mach number tables. Altitude may be converted to 
viscous parameter by use of Figure 4.0-1 (see also Append.x C). 
Where additional information is considered desirable, explanatory 
material has been provided in Appendices. 

These data are given in the following subsections: 

k.) LONGITUDINAL AERODYNAMIC CHARACTERISTICS ' 

4.2 LATERAL-D IRECTIONAL AERODYNAMIC CHARACTERISTICS 




VISCOUS INTERACTION PARAMETER 



4.0-1 



SD72-SH-.OOCO IM 



0$ 



Rockwell International 

Space Division 



4.1 LONGITUDINAL AERODYNAMIC CHARACTERISTICS.. Aerodynamic .chacacteri sti cs 
pertaining to the longitudinal .degrees .of . freedom-are. presented as full- 
scale rigid and elastic force and moment coefficients. The longitudinal 
aerodynamic coefficients are pres-ented in the following subsections: 

4.1 .1 BODY AXIS DATA 
4.1.2 STABILITY AXIS DATA 

Each subsection is then divided into the pertinent coefficients which are 
considered separately and prefaced by the appropriate equation for obtain- 
ing the total coefficient for -any selected flight condition. Each element 
of the equation is defined and referenced .to its associated figure (or 
table) for obtaining the corresponding numerical values, which comprise 
the remainder of the subdivisions. 

The aerodynamic data are based on wind tunnel test data . involving scale 
models at various attitudes, Reynolds numbers, and Mach numbers. The aero- 
dynamic axial and drag force coefficients have been basedon wind tunne 
test data of the 140A/B and 1 40C scale models havi ng- s i x-i nch (full-scale) 
eleven gaps and the short OMS pods. The data have- been corrected for 
Reynolds number (skin- friction) ■ along- the- TPS- design trajectory (14414.1) 
as shown in Figure 4.1-1. Skin friction drag and forebody axial force 
coefficients are shown on Figure 4.1-2. Corrections for outer-mold- line 
(OML) surface conditions (TPS tilesand protuberances) - are a> l so included 
as shown in Table 4.1-1 and Figure 4. 1-3: -• Base- drag- characteristics were 
computed using wind tunnel test measurements of fusel age- base pressure 
as given in Figure 4.1-4. 



4.1-1 



C7--3H- CCCO 



'1* 



Rockwell International 

Space Division 




1-2 



rc72-3H-oceo 1M 



0ilj Rockwell International 

Space Division 




PROTUBERANCES- 
aib DATA PROBES 
CREW ESCAPE DOOR HINGE 
RCS NOZZLE PORTS 
HECESSEO THERMAlGlASS 

{a) Wirtdlhuld 

(b)Gbi«rvaiioft Windo>-i 

(c)S.de Houh W.ndow 
SPANWiSE OaPS 

(o)V.rl.tal Toil* Redder 

(b)Elavon Seol Doon 

(c)Body lo Body Hap 

T-O UMBUICAl 

VENTS 

(o) Cargo 6oy 

tb) for-oro RCS 

(<) Cabin 

(d) OMS RCS 

(«) All Fiii«lQ9« 



SUoIOTAi ^^ 

TPS ROUGHNESS'"."' 



fOTA 



ne.aa'-'o»'«' -•■ i — 
l |*ca i ioi.T 



Hd^lm^ |H«.8 !ll».* |l07.S | »0.l I 73.6 ' 6i.a 



.R.f.r.„c. Ora-.n^: VL70-009028 tav. "3" - IPS Penetra t . » Mag,™ - DC U <*.-.. Ll,h^ i9 nc O.-b.-.T. 

«CP D200RS 3cse ! i nc t/ M ■• •'t 
VC7O-00WO2 " Wd-FuseUcje Ac : I v* .>" I S/i«», 5tru.t U r»I <>kin Cuccul Inter ace 

VC70-00O007 - R.«ulr e « n « - .irbl ,r Vent J , s u«. - :.«-»,« ,ur.u Cd^.rllMn,, 



4.1-3 



n '. 2 -:•:!!- oc cc im 




Rockwell International 

Space Division 




4.1-4 



CE72-3H-0C C JM 



'Jt 



Rockwell International 

Space Division 



AC, 



A c A, ASi! - C A 3 Ai E _ '-Abase 



5 = o r 
S8 58 




0.4 



Macii Number 
0.8 1.2 



1.6 



2.0 



p^^^~X^^i^~ h ^==^^Sf^^2^}j^S 



5,»=0° 



-0.01 






S,„ = 2690 U 2 
S. 4S r 436.7ft 2 




0.02 e 



AC* o.oi g ggfej 



'sr 




0.3 1-2 

Mach Number 




a== 



*..= 55' 



0.03fc 







effect'of speepbra 



a 



5 se =87.2° 



J 



4.1-5 



SL72-Sii-0Cec 1M 



'1* 



Rockwell International 

Space Division 




4.1-6 



SC72-SH-0CCC 1M 



€> 



Rockwell International 
Spac* Division 



'•.I.I BODY AXIS DATA. The longitudinal aerodynamic characteristics In the 
body axis system are: 

'4.1.1.1 NORMAL FORCE COEFFICIENT 

4.1.1.2 AXIAL FORCE COEFFICIENT 

'♦.1.1.3 PITCHING MOMENT COEFFICIENT 

l».1.1.l» TRIM AND STABILITY 

The pertinent equation for obtaining the total .coefficient for any given 
flight condition precedes the .presentation of data. . .Each .element of the 
equation is defined and referenced to the appropriate .fi guces and/or 
tables for obtaining the corresponding .numer I ca I values. Where addi- 
tional information is considered .beneficial (e.g. , aeroelastlc-deforma- 
tion, hypersonic viscous interaction, and -RCS . impingement) , Appendices 
have been included for reference. 




BODY AXIS SYSTEM 



4.1.1-1 



SD72-SH-0C6C IM 



w 



* 



Rockwell International 

Space Division 




«iATIV« WIND 



it. 1.1.1 NORMAL FORCE COEFFICIENT. The Orbiter Vehicle aerodynamic normal 

force coefficient is defined in this section. The basic aerodynamic 
normal force coefficient data are 
presented in three forms: 1 ) as a 
function of angle of attack and 
Mach number from M = 0.25 through 
M = 20; 2) as a function of angle 
of attack and the viscous inter- 
action parameter (V») from 0.005 
(equivalent to H = 13.6) through 
0.03 (equivalent to 300,000 feet , 

of altitude); and 3) as a function of angle of attack and altitude 
from 300,000 feet through 600,000 feet. Orbital aerodynamic charac- 
teristics are included in Appendix C. RCS jet thrust, thrust 
impingement, and flow field changes due to jet plumes are also _ 
included in this section [k. 1.1.1]. Uncertainties associated with 
the normal force characteristics are available in Section 6.0 

The RCS flow field Interaction data are presented as a contribution 
to the normal force (N) rather than the coefficient (C N ) since the 
terms due to jet thrust and impingement are independent of dynamic 
pressure and cannot, therefore, be normalized in the conventional 
manner CAUTION should be observed when applying these terms in the 
fliqht regime where the RCS is used in conjunction with th e> aerody- 
namic force (cf Section 3-6); i.e., the aerodynamic coeff. cient must 
be converted to a dimensional force before adding the RCS, flow field 
interaction effect (see also Appendix B) . 



The total normal force is: 



N 



TOTAL 



3" S C M + 

N TOTAL 

AESO 



"RCS 



*The total aerodynamic normal force coefficient is obtained by the 
fol lowing equation: 



N Te>IM . N 8A51C N ElE 



AERO 



+ UC M + AC N 



VATCft 



AILERON 



Ielevon* AC + ^ C N RU00 „ + AC N 



<»O0Y 

FLAP 



5P6EO 
BRAKE 



+ C N. It + \ § + AC N HEX + A \ r - + ^ojou/o AC Ns,lt 5 



where, 
C, 



N 



BASIC 



Basic, full-scale, freest ream, rigid 

body normal force coefficient. 
NOTE: 1 . Al 1 control surfaces neutral 
except <j sb ■ 25 



(Figures 4.1.1.1-1 
through-6) 



"Refer to Appendix when using digitized data. 



added to the total 



riOTE: The increment presented In ^i ^-u , d ^^.^ misal ignme nts. 



from above calculations to ac 



t.1.1 



D72 -SH- OOCC !M 



#1% 



Rockwell International 

Space Division 



AC, 



"ELEVATOR 



Change in normal force coefficient (Figures 4.1.1.1-7 

due to elevon (elevator) deflection, through -36) 
5 e , when inboard and outboard angles 
are equal . 

NOTE: 1. Partial span factor, K N , to be^igure 4. 1 . 1 . 1 -37) 
used for elevon-body flap inter- 
connect flight system where <5 e 
is limited to ±5" and inboard 
and outboard angles are not 
equal . 



AC V 



K N iC N 



'».f 5 .„ 



e s?». 



+ (1 " K N> AC N 



6 »•»,, 



AC. 



UltERON 



Change in normal force coefficient 
due to aileron deflection,. <5 a « 

-Th^Ne+(l-X )ACM ^ +K %^; (l " K ^ )ACNe «o]" ACH 



ELEVATOR 



AC. 



'BODY 
FLAP 



Change in normal force coefficient (Figures 4.1.1.1-38 

due to body flap deflection, 5 BF . through -66) 



AC ■ Change in normal force coefficient due 

Nrudoer t0 ru dder deflection, <S . 



(Assume zero) 



AC 



N5PEED 

BRAKE 



- Change in normal force coefficient (Figures 4.1.1.1-67 

due to speed brake deflection, 5 sa> through -93) 



' N a 



AC. 



<FLEX 



Change in normal force coefficient due 
to rate of change of angle of attack, 
a, (per radian) .' 

Change in normal force coefficient due 
to pitch rate, q, (per radian).* 

Change in normal force coefficient due 
to ae roe las tic deformation. 



(Assume zero) 



(Assume zero) 



AC, cos a + AC n sin a 

L.FLEX DflEX 

AC. - flexible lift increment 

•-FlEX 



AC D 



FLEX 



■ flexible drag increment 



(cf. Section 4.1 .2.1) 
(cf. Section 4. 1 .2.2) 



*For rotary derivative transfer equations see NASA SP-3070, "Summary of Trans- 
formation Equations and Equations of Motion Used in Free Flight and Wind 
Tunnel Data Reduction and Analysis," Gainer, T. G. , and S. Hoffman, Langley 
Research Center, Hampton, Virginia (1972). 



4.1.1.1-2 



SL72-SH-006C 1M 



0$ 



Rockwell Internationa! 

Space Division 



AC ■ Change in normal force coefficient (Figure A. 1.1. I -94) 
^landing ,j ue t0 fully extended landing gear. 

GlAR ' 

AC - Change in normal force coefficient (figures 4.1.1.1-95 

N |??tCT° due to proximity of ground, f (h/b) through -KM) 

NOTE: 1. See Section 3-4 for ground 

clearance and scrape attitude. 

AC - Change In normal force coefficient due 

Ns ' L I s to addition of SILTS pod. 

■ On 



poo 



- AC, cos a ♦ AC n sin a 

L SUTS U SHTS 

POO '00 

AC - SILTS pod lift increment (cf. Section 4.1.2.1) 
1-saTs 

AC ■ SILTS pod drag increment (cf. Section 4.1.2.2) 

DsilT5 
POD 

RCS flow field interactions have been subdivided into three components'. 

. 1. RCS JET THRUST (subscript JT) 

2. RCS JET PLUME IMPINGEMENT (subscript IMP) 

3. RCS JET PLUME EFFECT ON FLOW FIELD (subscript Jl) 

The effect of the RCS may be described as a dimensional normal force 
(pounds) in terms of the significant contributing elements by. 

M . n * Tn + AN + AN ] + q S[AC„ + AC., + AC U +■ AC ] 

N tCS N JT l SU*f "ftfvON UM »O0T'W H l N N El EVON N»QO* Ncown 



Jl 



HAP FlAP «i6'NG 

CAHfOvER 
2 SIOES 



where, 

N iT - Normal force resulting from number (cf. Appendix B) 

(n) of jets being f i red 

- L lN JiT ' n] - lb 

OJG 

NOTE: 1. OJG - operating jet group 

2. Values given in Figure B-! are 
for reference only 

N su „. - Normal force resulting from jet in- (Figure 4. I . 1 . 1-105) 

imp pingement on OV surface(s). 



LOW n ] - lb 



OjO imp 



4.1.1.1-3 



1M 



* 



Rockwell International 

Soace Division 



ANeuvon ■ Change in normal force due to effect (Figure 4. I . 1 . 1 -106) 



IMP 



AN 



»oov 

HAP 

IMP 



AC L 



AC, 



of impingement on elevon effective- 
ness . 



£[ 



3N 



o.o^T ' 



n ] - lb 



Change in normal force due to effect (Figure A. 1.1. 1-107) 
of impingement on body flap effec- 
tiveness . 



3N 
oTg " 3,5 »f 



Li- 



IF 



n ] - lb 



Change In normal force coefficient 
due to jet interaction. 

X>C N ] 



OJG 



Nj, 



» Change in normal force coefficient 
Ieievon j ue to j et interaction on elevon 

effectiveness. 



E[uc N ) St (£. 

OJG 1 «»tF e8E« 



0.75 



(Figures 4.1 .1 .1-108 
through -110) 



NOTE: 1. Down-firing jets 

6 < 0°, 6 a - -30* 

e e KEF 

5 > s , 6 - +10' 
e e« f F 

2. Si de-f i ring jets 

6 < 0°, 6 - -30 ! 

C e «EF 

6 > 0°, 5 - +10' 
e e« E F 



3. Up-f i ri ng jets 



(Figure 4.1.1.1 -111) 

(Figure 4.1.1.1-112) 

(Figure 4.1.1.1-113) 

(Figure 4.1.1.1-114) 

(No effect) 



4.1 .1 .1-4 



._ .2-c,;.-0060 IM 



4* 



Rockwell International 

Space Division 



AC 



N »O0Y 

FLAP 
Jl 



Change in normal force coefficient due 
to Jet interaction on body flap effec- 
tiveness. 

. <5 8F \ 0.75 

OJG 



^h\ 



(X) 

BF \^ m l 



NOTE: 1. Down-firing jets 



V o° 



Sbf- 



V — H..25' 



F >0° m 

2. Side-f i ring jets 

3. Up-f i ring jets 



AC 



Noown 

FIRiNG 
CARRYOVER 

)l 
2SIOE5 



Effect of carry-over between left- 
and right-down firing jet groups 
due to jet interaction. 



(Figure 4.1.1 .1-115) 

(No ef feet} 
(No effect) 
(No effect) 

(Figure 4.1.1 .1*116) 



3AC 



Nil 



NOTE: 1. *./♦_- (0.15^3/qJn 
J 

2. This term is zero when down- x 

firing jet group is inopera- 
tive on one side. 

3. (y5j "yO/Uo + ^j^ooU] 

where: <(*./? J < 0.03 
J 

The total RCS effect, N during thrust build-up and decay is 

obtained by reducing the full thrust value by the ratio of momentary 
thrust (see Ref. 4-3 ) to full thrust. 



4.1.1.1-5 



SD72- 



■ OCCC 



I ivi 



* 



Rockwell International 

Space Division 



L 



1.5 



U 




-0.5 



1.4 



W 



CONFIGURATION 



BASELINE 0R9ITER VEHICLE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO « BL 0.0 IN. 

MGttNT REFERENCE ZO « WL 375.0 IN. 



REFERENCE DI«:NSION5 

WING AREA SW - 2690.00 SQ.FT. 

WING SPAN BW « 78.055 FT. 

M A.C. CW = 39.560 FT. 

ROPY LENGTH IR - 1g90.3 IN. 



ALPHA (PEG) 



0.250 
A 



0.H00 

_B 



0.600 

c 



0.800 
D 



HACH 



0.850 



0.900 

F 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

SO. 000 

45.000 

50 -000 



-0.51500 

-0.27500 

-0.15500 

-0 . 05000 

0.06500 

0.18000 

0.30502 

0.41500 

0.53000 

0.65500 

0.80500 

0.96000 

1 . 07000 

1 . 18000 

# « * 

* •* 

* »* 

• • • 
lift 



-0.52400 

-0.28000 

-0.16500 

-0 . 05000 

0.06500 

0.18000 

0.30500 

0.42000 

0.54200 

0.67000 

0-81300 

0.97000 

1.08000 

1 . 18000 



0.54500 
0.29600 
0.17500 
. 05500 
. 07500 
0.18500 
0.31500 
0.43000 
0.56500 
0.70000 
0.84000 
0.99400 
.10000 
.16000 



» t t 
* * • 



unPM/u, rnerr r.nFFF lClEN 



0.920 
_S 



0.950 
H 



0.980 



-0.60500 

-0 . 33504 

-0.19500 

-0 . 06500 

0.06500 

0.19500 

. 33000 

0.46000 

0.59000 

. 72000 

0.84700 

0.97506 

1 . 03500 

1 . 05000 



>± 



• » ♦ 

• •• 

♦ * * 

# « * 



-0 
-0 
-0 
-0 



0. 

0. 

0. 



0. 

0. 



1 
I 



62000 
34600 
20000 
06200 
07000 
20000 
33000 
46000 
59400 
71500 
84000 
96000 
02000 
04000 



-0.63500 

-0.35500 

-0.21000 

-0 . 06000 

. 07500 

0.21200 

. 33800 

0.46700 

0.60000 

0.73000 

0.B5000 

0.98500 

1 . 03500 

1 . 08000 






-0.65500 

-0.36000 

-0.22000 

-0.06000 

. 08000 

0.22500 

0.36500 

0.50000 

0.62000 

0.75500 

0. 80500 

1.01000 

1 . 06000 

. 1 1500 

i i • 
»•* 

• * f 

• 4 t 



» » ► 



-0.6B500 

-0 . 37000 

-0.22000 

-0.06000 

. 09000 

0.25000 

0.40500 

■ 0.54500 

0.68500 

0.62000 

0.94000 

1 . 06500 

1 . 1 3000 

1 . 18000 

• • ♦ • 

• t ♦ » 
» » » # 

• * * * 

4 * • t 



69000 
.37500 
20500 
. 05500 
.10000 
.26000 
.41000 
.55000 
.70500 
.84000 
.97500 



1 . 11000 
1 . 19000 
1.25000 



F'OlNEER WM7. 



FIGURE 4.1.1.1-1 

BASIC NORMAL FORCE COEFFICIENT 



4.1.1.1-6 



SD72-dH-Cv6 1M 



* 



Rockwell International 

Space Division 



ALPHA CDEGD 

10 20 

I i l I 



z 
u 




1.2 1.3 l.H 

MACH NUMBER 



CONFIGURATION 



baseline 0R8HER vehicle: 

CENTER OF GRAVITY XO • FS 1076.7 IN. 

OR YO " BL 0.0 IN. 

MOfENT REFERENCE ZO « U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW « 79.055 FT. 
h.A.C. CW - 39.560 FT. 
BODY LENGTH IP • 1290.3 — U± 



ALPHA (CCG) 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20 . 000 

22.500 

25.000 

30.000 

35.000 

HO . 000 

H5.000 

so -ooo 



0.900 

F 



0.920 

_£ 



0.950 
H 



0.980 
J. 



MACH NLr-gcft 



1.050 



1.100 
K 



! .200 
_L 



1.300 

M 



I .500 

N 



-0.63500 

-0-35500 

-0.21000 

-0.06000 

0.07500 

0.21200 

0.33800 

0.H6700 

0.60000 

0.73000 

0.86000 

0. 96500 

1.03500 

1 . 08000 

• •» 

• *• 

• • » 

• » « 



-0.65500 

-0 . 36000 

-0.22000 

-0.06000 

0.08000 

0.22500 

0.36500 

0.50000 

0.62000 

0.75500 

0.88500 

1.01000 

1.08000 

1.11500 






-0 . 68500 

-0.37000 

-0.22000 

-0 . 06000 

. 09000 

0.25000 

O.H0500 

0.5M500 

0.68500 

0.82000 

. 9*000 

1 . 06500 

1.13000 

I .18000 



NOFnAL FORCE COEFFICIENT 



• I • 

• 1 « 

♦ 4 * 

* * * 



• #** 

* •* • 



-0.69000 
-0 . 37500 
-0.20500 
-0 . 05500 
0.10000 
0.26000 

o.mooo 

0.55000 
0.70500 
0.8hOOO 
0.97500 
1.11000 
1.19000 
I .25000 



* ftftftftfti 
•••• • • • 

• • » •« •« 
• • • •» • » 



-0.68500 

-0 . 3750C 

-0.21000 

-0. OH 700 

0.11000 

0.27000 

O.H1500 

0.57000 

0.71200 

0.85000 

0.98500 

1 .12000 

1.21500 

1.29500 






. 63000 
. 37200 
0.20000 
0.036O0 
0.11500 
0.27000 
O.H1500 
0.56500 
0.71200 
0. 84500 
0.98000 
1 . 12000 
.21500 
.29500 



-O.E5000 

-0 . 35000 

-0. 19000 

-0 . 02500 

. 1 1 1 70 

0.26500 

O.mOOO 

0.55200 

. 68700 

. 82500 

0.9H30C 

1 . C7000 

1.18000 

1.28000 



• «• 

• • • 

• •• 

• • • 



• •• 

• « » 

• • • 

• * * 



-0.6:500 

-0.32000 

-0. 17500 

-C . 02300 

0. 11000 

0.25500 

. 39500 

0.52500 

. 66500 

. 79000 

0.91500 

1.03500 

I . 1^000 

I .2^500 



-0.5c^.0u 

-0.25700 

-0. 13700 

-0.0! 500 

0. lOCOC 

0.23000 

. 35000 

0.46000 

. 59000 

070230 

0.62000 

0.93600 

! 0^=00 

1.15000 



• * • • 

• • ♦ • 
» » • • 

• » ♦ ♦ 

• » ♦ * 



ENG I NEE3 _y^J~ 
DATE Ct> ->£z.~)X 



FIGURE 4.1.1.1 -2 

BASIC NORMAL FORCE COEFFICIENT 



4.1.1.1-7 



SD72-SH-C06C 1M 



'1* 



Rockwell International 

Spae* Division 



ALPHA CDEGD 
-25 25 

I I I I I I I I I I I I I 



50 



2.0 



^--:::::t:: 




Mil 



! I 








P^S&^P^ 



-0.5 



.Mil 



n — TTT 








I I M 



MM 



I 1 M 



3.5 

NUMBER 



4.0 



4.5 



5.0 



5.5 



6.0 



" " COFIGURATJ0N 

BASELINE 0P8ITER VEHICLE 
CENTER Of GRAVITY XO - F5 1075.7 IN. 
OR YO » BL 0.0 IN. 

MOMENT REFERENCE ZO - W. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW ■ 2690.00 SQ.FT. 
MING SPAN 8W - 78.056 FT. 
M.A.C. CW ■ 39.560 FT. 



ROPY LENGTH IB - 1290.3 I 



N. 



ALPHA I PEG) 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

40.000 

45.000 

50.000 



1.100 
K 



1.200 

_L 



1.300 
M 



1.500 

N 



kach NLr-eea 



2.000 



2.500 

P 



-0.68000 

-0.37200 

-0.20000 

-0.03600 

0.11500 

0.27000 

0.4)500 

0.56500 

0.71200 

0.84500 

0.98000 

1.12000 

1.21500 

1.29500 



< • • 
»« 



-0.55000 

-0.35000 

-0.19000 

-0.02500 

0.11)70 

0.26500 

0.41000 

0.55200 

0.68700 

0.82500 

0.94300 

1.07000 

1.18000 

1 .28000 



-0.61500 

-0.32000 

-0.17500 

-0.02300 

0.11000 

0.25500 

. 39500 

0.52500 

0.66500 

0.79000 

0.91500 

1.03500 

1 .14000 

1.24500 



_NQRMAL FORCE COEFFICIENT 



3.000 
_Q 



4.000 
R 



5.000 
_£ 



-0.52500 

-0.26700 

-0.13700 

-0.01500 

0.10000 

0.23000 

. 35000 

0.46000 

0.59000 

0.70800 

0.O2000 

0.93800 

1.04500 

1 . 15000 



-0.40000 
-0.21000 
-0.10500 
.01700 
.09000 
17300 
.26000 
.35700 
0.45500 
0-55500 
0.66500 
. 77000 
0.87300 
0.97700 
1.20210 



«*»•••»»••»» 
•»»»»•»•••»* 



0.34310 
. 1 7870 
0.11000 
0.04290 
. 03500 
0. 1)480 
0.20480 
0.29370 
0.33280 
0.47560 
0.57440 
0.67240 
. 77000 
0.86270 
. 10420 



♦ ♦t * t * 



-0.32000 
-0.18000 
-0.11000 
-0.03700 
0.02500 
0.09500 
0.17000 
0.24500 
0.32200 
0.40200 
0.49000 
0.58500 
0.69000 
0.79000 
1 .01500 
1 .23500 
I .^6500 
1.70000 



-0.25260 
-0.14880 
-0.10500 
-0.04430 
0.01500 
0.06940 
0.13060 
0.19860 
0.27040 
0.35040 
0.43460 
0-52190 
0.60500 
0.71550 
0.92770 
1.14 130 
1.36490 
1.58950 



»*-•»•*»»* ►••#»#• ♦ • • 



-0.22130 
-0.13350 
-0.09500 
-0.04724 
0.01000 
. 04990 
C . 1 0700 
0.16700 
0.23390 
0.30690 
. 38900 
0.47500 
. 56500 
0.56000 
0.07000 
1 . 07900 
i . 30900 
1.52900 
1.7E303 



ENGINEER WV^I. 
OATE Z.^JLrJt -M 



FIGURE 

BASIC.; 



4.1.1.1 -3 
NHRHAl FORCE COEFFICIENT 



4.1.1.1-8 



SC72-SH-0C6 1 M 



€> 



Rockwell International 

Spae*Dtv«ion 



L "', 



ALPHA CDEG) 
20 20 40 60 

~l i | I II | ■ i i | ■ I ! | 



2.0 



1.5 



Z 

u 




-0.5 



CONF 1GLRAT ION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

or Yo - a. 0.0 IN. 

MCf£NT REFERENCE 2D - WL 375.0 IN. 



REFERENCE (DIMENSIONS 

WINS AREA SW « 2690.00 SO. FT. 

WING SPAN SW » 78056 FT. 

M.A.C. CW - 39.560 FT. 

9 QPY LENGTH IR ■ 1290.3 IN, 



ALPHA (CEG) 



10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

40.000 

45.000 

50 000 



2.000 
_Q 



2.500 

P 



3.000 
Q 



4.000 
R 



HACH NUT-BER 



5.000 



-0.40000 

-0.21000 

-0.10500 

-0.01700 

0.09000 

0.17300 

0.26000 

0.35700 

0.45500 

0.55500 

0.66500 

. 77000 

0.87300 

0.97700 

1.20210 



-0.34310 
-0.17870 
-0.11000 
-0.04290 
0.03500 

o.n^eo 

0.20H80 

0.29370 
0.38280 
0.47560 
0.57hm0 
0.67240 
. 77000 
0.88270 
1.10420 



-0.32000 
-0.18000 
-0.11000 
-0.03700 
0.02500 
0.09500 
0.17000 
0.24500 
0.32200 
0.40200 
0.^9000 
0.58500 
0.69000 
0.79000 
1.01500 
I .23500 
1 .46500 
1 .70000 



NpgfUL force ccerr 



-0.25250 
-0.14880 
-0.10500 
-0.04430 
6.01500 
0.06940 
0.13060 
0.19860 
0.27040 
0.35040 
0.43460 
0.52190 
0.60500 
0.71560 
0.92770 
1.14130 
1.36490 
1.58950 



-0.2213C 
-0.13350 
-0.09500 
-0.04724 
0.01000 
0.04990 
0.10700 
0.16700 
0.23390 
0.30690 
0.38900 
0.47500 
0.56500 
0-66000 
0.87000 
1.07900 
1.30900 
1.52900 
1-76303 



CiENT 



8.000 

_I 



10.000 

_y 



15.000 
v 



20 . 000 
W 



-0.20610 

-0.13270 

-0.09300 

-0.05540 

-0.01700 

0. 02390 

0.06380 

0.11870 

0.17850 

0.25C30 

. 33330 

0.41C00 

0.50500 

0.60000 

0.80800 

1.01900 

1 .24000 

1 .45800 

1.68500 



-0.20810 

-0.13270 

-0.09300 

-0.05540 

-0.01700 

0.02370 

0.06470 

0.11250 

0.17030 

0.24080 

0.32300 

CT.400C0 

0.H9500 

0.59000 

. 78000 

1.00000 

1.20500 

1 .43000 

1.66000 



-0 . 206 1 

-0.13270 

-0 . 09300 

-0 . 055m 

-0.01700 

0.02370 

0.06470 

0.11250 

0.17C30 

0.24C20 

0.32300 

0.400CO 

0.49500 

0.59000 

0.79000 

1.00000 

1 .20500 

1 .43000 

.1.6600? 



-0.20310 

-0.13270 

-0 . 0930C 

-0.055*0 

-0.01700 

0.C2370 

0.064 7C 

0.11250 

. 1 7030 

0.2*080 

0.32300 

0.40C00 

0.49500 

0.59000 

0.78000 

1 .00000 

1 .2C500 

1 .43000 



EN3 fNEER^JKlZ- 



i£.-78- 



FIGURE 4.1.1.1-4 

5ASIC NQRMAlj FORCE COEFFICIENT 



i. 1.1. 1-9 



(J ! ! -1 



*1* 



Rockwell International 

SpdC« Division 



2 
U 



ALPHA CDEG) 

20 30 40 



2.0 




.02 



i i I I I M I i i i i 1 i I I t I I I I i I I I I I I t I 1 I I I ) I ' I I I I M 1 I I ! I I 
.05 .06 -07 .08 .09 . 10* .11 -12 

VBAR 



.03 



.04 



COrf IGURAT ion 
BASELINE 0R91TER VEHICLE REFERENCE DIMENSIONS 

CENTER Of GRAVITY XO « FS 1075.7 IN. WING AREA SW « 2690.00 SQ.FT. 

OR YO-BL 0.0 IN. UING SPAN BK » 78.056 FT. 

MCTCNT REFERENCE ZO - UL 375.0 IN. M.A.C. CW • 39.560 FT. 

BODY LENGTH L9 = 1290.3 IN. 



ALPHA (OEG) 


VBAR 


0.005 

A 


0.010 
B 


0.020 

c 


0-040 
D 


0.050 
E 


0.080 
F 


VISCOUS NORMAL FORCE COEFFICIENT 


20.000 

25.000 
30.000 
35.000 
40.000 
. 45.000 
50 . 000 


0.40000 
0.59000 
. 78000 
1 . 00000 
1.20500 
1.43000 
1 .56000 


0.40000 
0.59C00 
0.78000 
1.00000 
I .20500 
1 .43000 
1 .66000 


0.40000 
0.59000 
0.78000 
1.00000 
1 . 20500 
1.43000 
1 .66000 


0.40000 
0.59000 
. 78000 
1 .00000 
1 .20500 
1.43000 
1 .56000 


0.40000 
0.59000 

o.7eooo 

1 .00000 
1 .20500 
1 .43000 
1 .56000 


0.40000 
0.59000 
. 78000 

1 . opooo 

1 .20500 
1 .43000 
I .56000 



ENGINEER NASA 
DATE ""--. 



FIGURE 4.1.1.1 -.5 
BASIC NORMAL FORCE COEFFICIENT 



4.1.1.1-10 



S L "/'•'- 3 H-PrfO IM 



4* 



Rockwell International 

Space Division 



ALPHA CDEGD 

20 HO 60 

I I I I | I I I I | 



a.o 



u 




350000 



H00000 



H50000 



500000 550000 600000 

ALTITUDE CFT. ] 



650000 



700000 



750000 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MGttNT REFERENCE 20 = UL 375.0 IN. 



REFERENCE DirENSIONS 
WING AREA 5W ' 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BODY I rNGTH LB ' 1290.3 IN. 





ALTITUDE (FT. 


) 




300000.0 


350000 . 


400000.0 


450000.0 


500000.0 


ALPHA (DEG) 


A 


8 


C 





E 




HIGH ALTITUDE NORMA] 


L FCRCE 


20 . 000 


0.40000 


0.43820 


0.47800 


0.49930 


0.50740 


• 25.000 


0.59000 


0.632S0 


0.67730 


0.701H0 


0.71020 


30.000 


. 78000 


0.83600 


0.99440 


0.92570 


0.93750 


35.000 


1.00000 


1 . 06630 


1.13530 


1.17230 


1.18630 


HO. 000 


1.20500 


1.29210 


1.38300 


1 .43160 


1.45000 


H5.000 


I .43000 


1.53190 


1.63820 


1 .59500 


1.71650 


50.000 


1 .66000 


I . 77500 


1 .89490 


1 .95900 


1 . 98330 



550000 . 

F 



6000GO.O 
G 



0.50990 
0.71310 
0.94180 
1.19070 
1 .45580 
1 . 72330 
1 .9SC90 



0.51030 
0.71350 
0.94180 
! . 19140 

1 .45670 
1 . 72440 
1 .99210 



ENGINEER NASA. 
DATE "Z 



FIGURE 4.1.1.1-6 

BAS TT NjnRMAl FARCE COEFFICIEN1 



4.1.1.1-11 



SL72-Sh-CCfcG i M 



#1* 



Rockwell International 

Space Division 



MACH NUMBER 



0.250 



DELE CCEG3 

50 -25 85 

I I I | 1 l 'I I | 



LU 

•z. 
u 

Q 



-.4 



II I i 



1^\ 



I I I I I I I I 1 



-20 




5 10 

ALPHA CDEG: 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZO » WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 



ENGINEER 
DATE./j 



ER DCO 





1 






ALPHA 


(OEG1 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE <DEG1 


A 


B 


C 





E 


F 


G 


H 






ELEV 


CM NORMAL F 


ORCE INCfiEM 


ENT 






-HO. 000 


-0.43913 


-0.42131 


-0 . 39900 


-0.38317 


-0 . 39973 


-0.42213 


-0.47498 


-0.52100 


-35.000 


-0.41452 


-0.40204 


-0.39100 


-0.38213 


-0.39352 


-0.42144 


-0.4S616 


-0.53170 


-30.000 


-0.39287 


-0.37981 


-0.37800 


-0.37910 


-0.38639 


-0.41568 


-0.49859 


-0.52393 


-25.000 


-0.37464 


-0.358H9 


-0.36300 


-0.36910 


-0.37909 


-0.4C568 


-0.50218 


-0.45592 


-20.000 


-0.35740 


-0.33401 


-0.34100 


-0.35122 


-0.36669 


-0.33282 


-0.41565 


-0.38199 


-15.000 


-0.30036 


-0.29684 


-o.2eeoo 


-0.29323 


-0.29272 


-0.28815 


-0.31274 


-0 . 30470 


-10.000 


-0.20985 


-0.20886 


-0.19000 


-0.19803 


-0.19817 


-0.19503 


-0.20S98 


-0.20728 


-5.000 


-0.10148 


-0 . 09832 


-0. 10000 


-0.09824 


-0.09894 


-0.09932 


-0.10844 


-0.10851 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.09619 


0.09299 


0.0S500 


0.09845 


0.08892 


0.09018 


. 09345 


0.08313 


10.000 


0.19437 


0.18846 


0.18800 


0.18530 


0. 18746 


0.19093 


0.19224 


0. 17445 


15.000 


0.28316 


0.27659 


0.29800 


0.27761 


0.28194 


0.28892 


0.29242 


0.27060 


20.000 


0.38399 


. 37924 


0.38200 


. 37370 


0.38180 


0.39292 


0.39415 


0.36894 



FIGURE 



4. 1. 1. 1- 

EFFECT OF 



7 

ELEVCN 



4.1.1.1-12 



SD72-SH-0C-C 1M 



* 



Rockwell International 

Space Division 



[i 



MACH NUMBER 



0.400 



Q 




5 10 

ALPHA CDEG3 



CONFIGURATION 



BASEL INE ORB ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MOENT REFERENCE 20 = W_ 375.0 IN. 



REFERENCE 01 (PENSIONS 
WING AREA SW = £690.00 SQ.FT. 
WING SPAN 8W = 78.056 FT. 
M.A.C. CW = 33.560 FT. 

BOOY LENGTH LB = 1230.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5 . 000 


0.0 


5.000 


10.000 


15.000 


20.000 


25 . 000 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREtt 


ENT 






-40.000 


-0.43913 


-0.42131 


-0 . 39900 


-0.38317 


-0.39973 


-0.42213 


-0.474S3 


-0.52100 


-35.000 


-0.41452 


-0.40204 


-0.39100 


-0.38213 


-0 . 39352 


-0.42144 


-0.49616 


-0.53170 


-30 . 000 


-0.39287 


-0.37981 


-0.37800 


-0.37910 


-0.38639 


-0.41663 


-0.49S53 


-0.52393 


-25.000 


-0.37454 


-0 . 35849 


-0 . 35300 


-0.36910 


-0 . 37909 


-0.40568 


-0.50319 


-0.45592 


-20 . 000 


-0 . 35740 


-0.33401 


-0.34100 


-0-35122 


-0 . 35569 


• -0 . 3e£82 


-0.41535 


-0.381S9 


-15.000 


-O. 30036 


-0.29684 


-0.28800 


-0.29323 


-0.29272 


-0.23816 


-0.31274 


-0.30470 


-10.000 


-0.20985 


-0.20886 


-0.19000 


-0.19803 


-0.19317 


-0.19503 


-0.20988 


-0.20728 


-5.000 


-0.10148 


-0 . 09832 


-0.10000 


-0 . 09824 


-0 . 0S8S4 


-0 . 09932 


-0 . 1 0844 


-0.I085I 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.09619 


0.09299 


0.09500 


0.08845 


. 06892 


0.09018 


. 09345 


0.08313 


10.000 


0.19437 


0.18846 


0.18800 


. 1 S530 


0.18746 


0.19093 


0.19224 


0.17445 


15.000 


0.23315 


0.27859 


0.28300 


0.27761 


0.28194 


0.28892 


0.29242 


0.27C50 


20.000 


0.38399 


0.37924 


0.3820C 


. 37370 


0.38180 


0.39292 


0.3S415 


0.36894 



ENGINEER OC.CI 

OATE./p.-r-fr.^: 



FIGURE 



4.1. 1.1- 
EFFECT OF 



8 

ELEVGN 



4.1.1.1-13 



SD72-SH-0CC0 ]■;.[ 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



0.600 



DELE CDEG) 
50-25 o as 



LU 

u 

Q 



I I i'l 1 I | 1 I 



V-^&2 




^n 



c , I ! I I I I I 1 I I I I I I I M l l I ' .1 I I I I ' I M I I i I M I I I I I ,L 
'-20 -15 -10 -5 5 10 15 20 

ALPHA CDEG3 



i i I I 



25 



30 









CONFI 


OJRAT 


BASELl!^ ORBITER VEHICLE 






CENTER OF GRAVITY 


XO « FS 


1076 


7 


IN. 


OR 


YO 


■ 8L 








IN. 


MOMENT REFERENCE 


ZO' 


■ U. 


375 





IN. 



AT ION 




REFERENCE DIMENSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW » 78.056 


FT. 


M.A.C. CW = 39.560 


FT. 


BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


I DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREM! 


:nt 






-40.000 


-0.45821 


-0.38280 


-0.34200 


-0.34335 


-0.36044 


-0.33661 


-0.37852 


-0.29746 


-35 . 000 


-0.44113 


-0.37589 


-0.34000 


-0.34639 


-0.36467 


-0.34859 


-0.38564 


-0.30/30 


-30 . 000 


-0.41817 


-0.36301 


-0 . 33600 


-0.34055 


-0 . 36004 


-0 . 35454 


-0.39804 


-0.31301 


-25.000 


-0.38637 


-0.34758 


-0.33000 


-0.32960 


-0 . 34940 


-0.36029 


-0.37779 


-0.30755 


-20 . 000 


-0.33882 


-0.31422 


-0.30600 


-0.31258 


-0 . 33229 


-0.34625 


-0.34609 


-0.28920 


-15.000 


-0.2B113 


-0.26555 


-0.26100 


-0.26364 


-0.28495 


-0.27580 


-0.25369 


-0 . 24799 


-10.000 


-0.19673 


-0.19t37 


-0.1 8600 


-0.19062 


-0.19551 


-0.19427 


-0.17839 


-0. 17164 


-5.000 


-0.09645 


-0.0S651 


-0.0S50O 


-0.09408 


-0.09877 


-0.09283 


-0.09107 


-0 . 08673 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.08309 


0.09499 


. 09000 


. 09360 


0.09801 


. 09882 


0.08680 


. 07322 


10.000 


0.17434 


0.18148 


0.18300 


0.1 6873 


0.20495 


0.19069 


0.18121 


0. 13917 


15.000 


0.25839 


0.26546 


0.26500 


0.27827 


0.30470 


0.28063 


0.27033 


0.20593 


20 . 000 


0.34613 


0.34229 


0.34400 


. 36C92 


. 39895 


. 33484 


0.33740 


0.26332 



ENGlrCER OCcd 



FIGURE 4.1.1.1-9 
EFFECT OF ELEVCN 



4.1.1.1-U 



D72-SK-0060 I M 



#Jt 



Rockwell International 

Space Division 



i- 



MACH NUMBER 



UJ 

u 

Q 




5 10 

ALPHA COEG) 



CONFIGURATION 


BASEL IKE ORB ITER VEHICLE 


REFERENCE 0IMEN5ICNS 


CENTER OF GRAVITY XO =■ FS 1076.7 IN. 


WING AREA SW = 26S0.00 SQ.FT. 


OR YO * BL 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOf-£NT REFERE. k CE ZO = U. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1390.3 IN. 



1 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (CEG! 


A 


8 


c 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCRcMI 


;nt 






-HO. 000 


-0.45183 


-0.44512 


-0 . 39300 


-0.37583 


-0 . 364S5 


-0.27S29 


-0. 19060 


-0. 13576 


-35.000 


-0.43827 


-0.41726 


-0 . 37200 


-0 . 35635 


-0 . 33977 


-0.26113 


-0.18962 


-0. 14S59 


-30 . 000 


-0.41892 


-0.37835 


-0.34400 


-0.33197 


-0 . 30952 


-0.24209 


-0. 1SS48 


-0. 15361 


-25.000 


-0 . 3S876 


-0 . 33958 


-0 . 30700 


-0.30023 


-0.27385 


-0.22393 


-0. 18734 


-0. 16591 


-20 . 000 


-0 . 337S5 


-0.29984 


-0 . 2S300 


-0.26424 


-0 . 2364 1 


-0.20525 


-0. 18449 


-0. 15367 


-15.000 


-0.25971 


-0.24331 


-0.21300 


-0.22734 


-0.20191 


-0.19014 


-0 . 1 7762 


-0.16530 


-10.000 


-0.16762 


-0.18193 


-0.16000 


-0.17433 


-0.16527 


-0. 16515 


-0. 15448 


-0. 14549 


-5.000 


-0.0B751 


-0.10465 


-0 . 09500 


-0.10105 


-0 . 097C6 


-0 . 09780 


-0.08091 


-0.08450 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 07767 


0.09507 


. 09400 


0.09967 


. 0S996 


. 09522 


. 06552 


0.07006 


10.000 


0.15165 


0.17966 


0.18400 


0.201S5 


0.19035 


0.18638 


0.16801 


. 1 2454 


15.000 


0.21979 


0.24666 


0.27400 


0.28254 


0.25728 


0.25172 


. 23959 


. 1 7228 


20 . 000 


0.282=8 


. 30725 


. 32200 


0.35291 


0.3201 1 


0.29525 


0.29235 


0.2CS58 



ENGINEER Q.CO 
OATE/j>r2y^2Jl- 



FIGURE 4.1.1.1-10 

EFFECT OF ELEV.GN 



4.1.1.1-15 



SE 



/ .. - 



0C-6C IM 



'i* 



Rockwell International 

Spaca Division 



MACH NUMBER 



0.900 



DELE CDEGD 

-25 



lU 

2 




ALPHA CDEG) 



CONFIGURATION 



BASELINE CR3ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO « M. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW - 39.550 FT. 

BODY LENGTH LB » 1290.3 IN. 











ALPHA 


COEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE tOEG) 


A 


B 


C 





E 


F 


G 


H 




" 


ELEV 


ON NORMAL F 


CRCE INCREM 


ZHT 






-HO. 000 


-0.43671 


-0.39521 


-0.38200 


-0.39159 


-0.28104 


-0.17952 


-0.13469 


-0.11600 


-35.000 


-0.42534 


-0.38535 


-0 . 37300 


-0.36341 


-0.25133 


-0.16993 


-0.15595 


-0.13046 


-30.000 


-0.41008 


-0.36355 


-0 . 35300 


-0.32898 


-0.21880 


-0.16034 


-0.17139 


-0.14332 


-25.000 


-0.38201 


-0 . 32962 


-0.32000 


-0.28619 


-0.18798 


-0.15198 


-0.18368 


-0.15256 


-20.000 


-0.33795 


-0.28589 


-0. 27600 


-0.23734 


-0.15521 


-0.14310 


-0.18884 


-0.15610 


-15.000 


-0.28066 


-0.23188 


-0.22800 


-0.18425 


-0.12652 


-0.13074 


-0.18284 


-0.15271 


-10.000 


-0.17467 


-0.16729 


-0.16200 


-0.12409 


-0 . 09399 


-0.11162 


-0.15158 


-0.12974 


-5.000 


-0.08182 


-0.09187 


-0.08000 


-0 . 05275 


-0 . 05674 


-0 . 06737 


-0 . 07892 


-0.C5703 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 06386 


. 08002 


. 07000 


0.07741 


0.08156 


0.09109 


0.07122 


. 05704 


10.000 


0.13S75 


0.1 4046 


0.14500 


0.18366 


0.19215 


0.18470 


0.15550 


0.11514 


15.0G0 


0.19762 


0.19936 


0.21700 


0.27138 


0.27255 


0.25146 


0.22983 


0.15719 


20 . 000 


0.23479 


0.25665 


0.28500 


0.34096 


0.33459 


0.29020 


0.29290 


0.18452 



ENGINEER DCO 
DATE.Zfl r j?r5J/I- 



FIGURE 



4. 1.1. 1- 

EFFECT OF 



11 

ELEVCN 



4.1.1.1-16 



SL72-3n-0C6 1M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 



0.950 



DELE COEGJ 

-50 -35 25 

ri n 



UJ 

■z. 
u 
o 



-.2 



-.4 



-.5 



i I I 



I i I 



TTTT 



i i ■ i 




"R ' i T 



i I I I 1 ! I 1 I I I I i I I I I I I I I I I I I I I 



! ,1 I 1 I I 



i I ! I I I I i I 



-20 



-15 



-10 



5 10 

ALPHA CDEGD 



15 



20 



25 



30 



CONFIGURATION 




BASELINE 0R81TER CHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






ELEV 


ON NCRMAL F 


CRCE INCREM. 


ENT 






-HO. 000 


-0.43785 


-0 . 38S86 


-0.37300 


-0.40455 


-0.29111 


-0.19174 


-0. 14469 


-0 . 1 3322 


-35.000 


-0.42016 


-0.38209 


-0 . 37500 


-0.38567 


-0.27193 


-0.18301 


-0.16150 


-0. 14711 


-30 . 000 


-0.39915 


-0.36441 


-0.36700 


-0.35579 


-0.25156 


-0 . 1 7342 


-0. 17643 


-0.15786 


-25.000 


-0.36890 


-0.33365 


-0.34500 


-0.31697 


-0.22541 


-0.16067 


-0.18657 


-0.16633 


-20.000 


-0 . 32353 


-0.29388 


-0 . 30900 


-0.26706 


-0.19065 


-0.14419 


-0.19106 


-0.16805 


-15.000 


-0.24834 


-0.24605 


-0.2S000 


-0.20517 


-0.15235 


-0.12880 


-0.17874 


-0.15780 


-10.000 


-0.16788 


-0.18423 


-0.19300 


-0.13821 


-0.10813 


-0.10396 


-0.13524 


-0.12364 


-5.000 


-0 . 08576 


-0.09166 


-0 . 09500 


-0.06475 


-0 . 05744 


-0 . 05894 


-0 . 07052 


-0 . 06459 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 06963 


0.05180 


. 05000 


. 06450 


0.07467 


Q . 07724 


0.07694 


. 06539 


10.000 


0.14152 


0.09737 


0.11300 


0.14871 


0.17373 


0.15507 


0.14731 


0.11187 


15.000 


0.18891 


0.15731 


0. 18400 


. 22850 


0.25591 


0.21674 


0. 19797 


0.15089 


20 . 000 . 


0.22555 


0.22S86 


0.25500 


0.31116 


. 32306 


0.26759 


0.24 IC4 


0. 18329 



ENGINEER 

DATE7A 



R DCO 
-#z?±ZZ 



FIGURE 



4. 1. 1.1- 
EFFECT OF 



12 

ELEV0N 



4.1.1.1-17 



0\ffl Rockwell International 
SpaceDwision 



MACH NUMBER 



0.980 



DELE CDEGD 

-50 -25 25 

i I I I | I t I I | I I 1 



UJ 

z 

H 




-.a 



ALPHA CDEG) 



CCNFI 


GLft 


8ASEL1K£ CRBITER VEHICLE 




CENTER OF GRAVITY XO - FS 1076.7 


IN. 


OR YO * BL 0.0 


IN. 


MOMENT REFERENCE ZO - U. 375.0 


IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN 6W = 78.056 FT. 
M.A.C. CW = 39.560 FT. 
9QOY LENGTH LB * 1290.3 IN. 



DELE (PEG) 



-40.000 

-35.000 

-30 . 000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

CO 

5.000 

10.000 

15.000 

20.000 



ALPHA (PEG) 



-10.000 
A 



-5.000 1 
B 



0.0 

C 



5.000 




0.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



ELEVON NORMAL FORCE INCREMENT 



-0.43505 
-0.41526 
-0.39249 
-0.36054 
-0.31512 
-0.24371 
-0.16610 
-0.06533 
0.0 

0.07312 
0.14396 
0.16514 
0.21324 



-0.38064 
-0.37411 
-0.35826 
-0.33272 
-0.29506 
-0.24835 
-0.17735 
-0.08299 
0.0 

0.05191 
0.10003 
0.15588 
0.20940 



-0 . 36669 
-0.36699 
-0.36370 
-0.34625 
-0.30991 
-0.24602 
-0 . 1 7902 
-0.08718 
0.0 

. 05050 
0.11294 
0.18123 
0.25848 



-0.38965 

-0 . 37964 
-0.35961 
-0.32530 
-0.27232 
-0.20621 
-0.13513 
-0 . 05766 
0.0 

0.06311 
0.14466 
0.22281 
0.31041 



-0. 
-0. 
-0. 

•-o 

-0 

-0 

-0 

-0 













29178 
28401 
.26759 
24218 
,20542 
, 16304 
,11385 
.05714 
.0 

.07347 
.16598 
.24909 
.32234 



-0. 

-0. 

-0. 

-0. 

-0. 

-0. 

-0 

-0 








20475 
19546 
.18437 
.16959 
.15082 
.13086 
.10235 
.05611 
.0 

.07384 
.14987 
.21367 
.27230 



16043 
17064 
17888 
18469 
18037 
16605 
12568 
0.06716 
0.0 

0.07674 
0. 14194 
0.18710 




-0.15337 
-0.16C57 
-0.16495 
-0.1680! 
-0.16625 
-0.15159 
-0.11835 
-0.05353 
0.0 

. 06498 
0.11108 
0.14882 
0.18354 



ENGINEER PC9 
DATe_/ftr}<[r_'2£. 



FIGURE 



4. 1.1.1- 
EFFECTGF 



13 

ELEVON 



fc. 1.1.1-18 



SD72-SH-0060 I M 



* 



Rockwell International 

Space Division 



X 



MACH NUMBER 



1.050 



DELE CDEGD 

-50 -25 



25 



I i I l I'll 



UJ 

z 
a 
a 



-.2 



-.4 



-.6 



I I I l 



i i i i iii! i i ' i I i i i i I i ; i i | i i i i 



?£iz^J?* 




K" 



I I I I 



4^* 



^- B rf>2§i=^§=3«-'^-i ;= — 3=5-^^1 



Mill 



i I i I I I I I I I ! I I I I I 



I 1 1 i I 



. 1 I I I ..1 



-20 



-15 



-10 -5 5 10 

ALPHA C0EG3 



15 



20 



25 



30 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE D1NCNSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


MON£NT REFERENCE ZO = U- 375.0 IN. 


M.A.C. CW • 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 



ENGIN£ER_Q<10 
DATE7_ar2rl7l*.- 



FIGURE 4.1.1.1-14 

EFFECT GF ELEVCN 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELE (CEG> 


A 


9 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREM 


^NT 






-HO. 000 


-0.42587 


-0 . 35449 


-0.35100 


-0.34386 


-0.32737 


-0.24037 


-0.2C900 


-0.20615 


-35.000 


-0.40264 


-0.35013 


-0 . 34600 


-0.34209 


-0.31219 


-0.22918 


-0.19354 


-0.19614 


-30.000 


-0.37657 


-0 . 33933 


-0 . 337C0 


-0 . 33340 


-0.28925 


-0.21335 


-0.18557 


-0.18340 


-25.000 


-0 . 34059 


-0 . 32044 


-0.31300 


-0 . 30952 


-0.25820 


-0.19436 


-0.17138 


-0.16913 


-20 . 000 


-0.29525 


-0.28413 


-0.27600 


-0.25357 


-0.21B22 


-0 . ! 7226 


-0.15339 


-0.15171 


-15.000 


-0.23551 


-0.23309 


-0.20900 


-0.19074 


-0. 17110 


-0.13834 


-0.13164 


-0.129B2 


-10.000 


-0.15399 


-0.15143 


-0.14000 


-0.12573 


-0.1 1690 


-0.09958 


-0.10356 


-0. 10166 


-5.000 


-0.C8386 


-0 . 05548 


-0 . 06200 


-0.06475 


-0.05531 


-0.05192 


-0.06054 


-0.06155 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.C3136 


. 05960 


0.05700 


. 06099 


0.07276 


0.C6S81 


0.06871 


. 06476 


10.000 


0.14645 


0.11984 


0.12300 


0.14226 


0.15194 


0. 14309 


0. 12S43 


0.11021 


15.000 


0.17799 


0.15774 


0.16500 


0.22231 


0.23-455 


0.21907 


0.17350 


0.14631 


20 . 00C 


0.IS4S5 


0.17153 


0.24900 


0.32481 


0.32445 


0.29976 


0.21253 


0.1852S 



*» 

£ 



4.1.1.1-19 



€> 



Rcckwsli International 

Space Division 



MACH NUMBER 



1. 100 



DELE CDEGD 

50 -25 25 

TTTTTT 



a 




o 5 10 

ALPHA CDEG3 



COt^IGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO = 8L 0.0 IN. 

MOfENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2590.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW * 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (DEG! 


A 


8 


C 





E_... 


F 


G 


H 




ELEVON NORMAL FORCE INCREMENT 


-HO. 000 


-0.422H5 


-0 . 36322 


-0.35000 


-0.33269 


-0.28531 


-0.231S4 


-0.20355 


-0.20179 


-35.000 


-0.3S996 


-0.35871 


-0.33400 


-0.30896 


-0.2703! 


-0.21488 


-0.18973 


-0.18584 


-30.000 


-0.36836 


-0.33799 


-0.31000 


-0.28613 


-0.25423 


-0.19417 


-0.17295 


-0.17147 


-25.000 


-0.32670 


-0.30312 


-0.27900 


-0.25830 


• -0.23103 


-0.17304 


-0.15583 


-0.15431 


-20.000 


-0. 27544 


-0.25719 


-0.23400 


-0.22041 


-0.198S0 


-0. 14895 


-0.13703 


-0 . 1 3487 


-15.000 


-0.21885 


-0.20018 


-0.18200 


-0.17331 


-0.15670 


-0.12353 


-0. 11505 


-0 . 1 1 344 


-10.000 


-0.15302 


-0.13251 


-0.12000 


-0.12214 


-0.10537 


-0.09262 


-0.08781 


-0.08772 


-5.000 


-0.07987 


-0.05610 


-0 . 05500 


-0 . 05678 


-0 . C4959 


-0.04947 


-0.05171 


-0.05318 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.05285 


0.05406 


. 05300 


0.05792 


0.06685 


. 05908 


. 05870 


0.06031 


10.000 


0.10311 


0.11092 


0.1 1 100 


0. 12904 


0.14291 


0.12963 


0.12432 


0.IC503 


15.000 


0.13S43 


0.15232 


0.15700 


0.1S325 


0.22956 


0.19105 


0.16433 


0.14334 


2O.0C0 


0.16294 


0.1S559 


0.22300 


0.25715 


0.31697 


0.2^926 


0.19755 


0.178H0 



ENGINEER DC O 
DATZ/A.z'3rzT£ZZ 



FIGURE 



4. 1.1.1- 

EFFECT OF 



15 

ELEVON 



4.1.1.1-20 



.«= r t 



E72-SH-CC6C I M 



#1% 



Rockwell International 
Space Division 



MACH NUMBER 



DELE CDEG) 

50 -25 (3 25 

! I I ; I i i I ! I I i i I 



LU 

2 
CJ 
Q 



-.4 




5 10 

ALPHA CDEG) 



CONFIGURATION 



BASELINE CffBITER VEHICLE 
CENTER OF GRAVITY XO =• FS 1076.7 IN. 
OR YO « BL 0.0 IN. 

MOMENT REFERENCE ZO - W. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2SSC.00 SQ.FT. 
WING SPAN BW » 78.055 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB - 1890.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


8 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


0RCE INCREM 


INJ 






-40.000 


-0.41251 


-0.37195 


-0 . 33900 


-C 29593 


-0 . 25232 


-0.223C3 


-0. 19215 


-O. 13305 


-35.000 


-0.37869 


-0.33885 


-0.30700 


-0.27007 


-0.23445 


-0.20214 


-0.17653 


-0 . 1 7302 


-30.000 


-0 . 33655 


-0 . 30376 


-0.27500 


-0.24123 


-0.21255 


-0.18025 


-0.16189 


-0.16025 


-25.000 


-0.28878 


-0.26525 


-0.23900 


-0.21239 


-0.1 8833 


-0.15740 


-0. 14404 


-0.14523 


-20.000 


-0.23736 


-0.21876 


-0.19700 


-0.17857 


-0.16000 


-0.13332 


-0.12518 


-0.12820 


-15.000 


-0 . 1 7842 


-0.16405 


-0. 14800 


-0.13950 


-0.12658 


-0.10705 


-0. 10423 


-0 . 1 0754 


-10.000 


-0. 11846 


-0.10851 


-0. 10000 


-0 . 09429 


-0.09066 


-0 . 07540 


-0.07715 


-0.08122 


-5.000 


-0 . 05082 


-0 . 05447 


-0.04900 


-0.04778 


-0.04831 


-0 . 04393 


-0 . 04552 


-0.04766 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 04980 


0.04617 


. 04600 


0.04782 


0.05810 


. C5399 


0.04930 


0.05431 


10.000 


0.10004 


0.09971 


. 09500 


0.10578 


0.12460 


0.12507 


0.10075 


0.09913 


15.000 


0.13689 


0.13595 


0.14200 


0. 16574 


0.18624 


0. 18994 


0.15072 


0.13198 


20 . 000 


0.16147 


0.17207 


0.18700 


0.23020 


. 23854 


. 24e33 


0. 19474 


0. 15492 



ENGINEER.PQ 

OAJZyAli 



FIGURE 4.1.1.1-16 

EFFECT OF ELEVQN 



4.1.1.1-21 



Rockwell International 

Space Division 



MACH 



LU 

z 
<_> 
a 



-.2 



-.4 



-.6 



NUMBER 

till 



1.300 



DELE 

■50 -25 

| I I I I | I I 



CDEG) 


T"T 



25 




I I I I I 







I 1 I I 1 



1 ! I I L l.il 



l I ' 



< I ■ 



-20 



-15 



-10 



5 10 

ALPHA CDEG) 



15 



20 



25 



COFIGLRATICN 




BASELINE CRSITER VEHICLE 


REFERENCE OihCNSIONS 




CENTER OF GRAVITY XO - FS 107S.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MO-ENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB =■ 1290.3 


IN. 



ENGINEER 



*t 



FIGURE 



4. 1. 1.1- 
EFFECT OF 



17 

ELEVGN 



30 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 




ELEV 


ON NORMAL F 


ORCE INCREK 


:nt 






-i+O.OOO 


-0.40065 


-0.31526 


-0.27000 


-0.24326 


-0.21464 


-0.19085 


-0.17821 


-0.16914 


-35.000 


-0.35130 


-0.28554 


-0.24600 


-0.22923 


-0.196S5 


-0.17769 


-0.17033 


-0.16204 


-30.000 


-0.31813 


-0-25278 


-0.21700 


-0.21017 


-0.17692 


-0.15507 


-0.16138 


-0-15219 


-25.000 


-0.26987 


-0.21518 


-0.18600 


-0.17921 


-0.15775 


-0.14065 


-0.14829 


-0.13941 


-20 . 000 


-0.21940 


-0.17458 


-0.15100 


-0.14533 


-0.13153 


-0.12166 


-0.13222 


-0.12461 


-15.000 


-0.16724 


-0.12814 


-0.11400 


-0.11122 


-0 . 1 0752 


-0.09693 


-0.11089 


-0.10507 


-10.000 


-0.1C825 


-0.08486 


-0.07500 


-0.07415 


-0.07554 


-0.06628 


-0.C8338 


-C. 08 190 


-5.000 


-0.05573 


-0.03873 


-0.03600 


-0.03786 


-0.03846 


-0 . 03704 


-0 . 04H24 


-0.04551 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.04403 


0.04407 


0.04000 


. 04070 


0.05233 


0.04883 


0.04995 


0.05034 


JO.OOO 


0.07644 


0.08151 


. 07800 


. 08659 


. 099H3 


. 0S690 


. 1 0254 


0.08962 


15-000 


0.10316 


0.12474 


0.12300 


0.13914 


0.15C81 


0. 14716 


0.12755 


0.11669 


20.000 


0.12451 


0.16563 


. 1 7600 


0.19992 


0.19961 


0.19878 


0.1485! 


0.12363 



4.1.1.1-22 



* 



Rockwell International 

Space Division 



L 



MACH NUMBER = 1.500 

■'♦i i i i i i i i i i | n i i I i i i i I , i i 



UJ 

■z. 
u 

Q 



-.a 



-.4 



-.6 



T 



1^ 



I I I I I I I I I I I I I I I I I I I 1 I I 



111! 



DELE CDEG] 

-50 -25 25 

| I I I I | I I I ! | I ! I i | 

( I I I i II I 1 I I i I l I i ' 




r 



f i i i i i i ■ i i i i i i 



i i ' i 1 1 



-20 -15 -10 -5 5 10 

ALPHA CDEG) 



15 



20 



25 



30 



COM 1- 1 C3URATION 




BASELINE ORBITER VEHICLE 


REFERENCE 01 MENS IONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 73.056 


FT. 


MOMENT REFERENCE 20 » WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 



ENGINEER OC.Q 



FIGURE 



4. 1.1.1- 

EFFECT OF 



18 

ELEVCN 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


e 


C 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREMENT 






-40.000 


-0.25125 


-0.21725 


-0.22071 


-0.19612 


-0 . 1 7532 


-0.16659 


-0.15336 


-0.15770 


-35.000 


-0.22801 


-0.20330 


-0.20103 


-0.17790 


-0. 16070 


-0.15405 


-0.15087 


-0.1505= 


-30 . 000 


-0.20137 


-0.18340 


-0.17821 


-0.15874 


-0.14707 


-0.14440 


-0.13551 


-0 . 1 3992 


-25.000 


-0. 17106 


-0. 15959 


-0.15060 


-0.13548 


-0.13110 


-0.12940 


-0.12074 


-0.12480 


-20.000 


-0.14064 


-0.13187 


-0.12363 


-0.11373 


-0.10488 


-0.10660 


-0.09949 


-0. 10050 


-15.000 


-0.10753 


-0.10041 


-0.09235 


-0 . 03807 


-0.08121 


-0.08550 


-0.07835 


-0.07918 


-10.000 


-0.07579 


-0 . 06755 


-0.06076 


-0.05955 


-0.05491 


-0 . 053S0 


-0.05308 


-0.05379 


-5.000 


-0.03813 


-0.03301 


-0 . 03029 


-0.03216 


-0.02719 


-0.02347 


-0.02701 


-0.02738 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.03125 


0.03211 


0.03005 


0.03169 


. 03760 


. 04289 


0.04853 


0.05294 


10.000 


0.05952 


. CS557 


. 06064 


0.06568 


. 07686 


0.085S9 


0.09753 


. 1 080 1 


15.000 


0.09217 


0.09323 


o . ossao 


0.10167 


0.11125 


0.13012 


0.15163 


0.17033 


20.000 


0.12451 


. 1 1 5S9 


0.12316 


0.14173 


0. 144=8 


0. 17747 


0.20751 


0.23068 



4.1.1.1-23 



SD72-SK- QCCC 



€* 



Rockweil International 

Space Division 



MACH NUMBER 



2.000 



DELE CDEG) 

-50 -25 25 



a 




CONFIGURATION 



BASELINE (OBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MCftNT REFERENCE 20 - W. 375.0 IN. 



REFERENCE OII^NSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW « 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB =■ 1290.3 IN. 









ALPHA (DEG) 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30 . 000 


DELE <0EG> 


A 


3 


C 





E 


F 


G 


H 


I 








ELEVON NOR 


MAL FORCE I 


NCREf-£NT 








-HO. 000 


-0.13S82 


-0.12580 


-0.11500 


-0.10225 


-0.09640 


-0.09982 


-0 . 1 0653 


-0.11 097 


-0.11843 


-35.000 


-0.13130 


-0.11970 


-0.11000 


-0.09285 


-0.09127 


-0 . 09673 


-0.10500 


-0.10378 


-0. 10987 


-30 . 000 


-0.1 1887 


-0.10961 


-0.10300 


-0.C8545 


-0.08336 


-0.C8952 


-0.09560 


-0.09301 


-0.09958 


-25.000 


-0.10365 


-0 . 09959 


-0 . 09300 


-0 . 07584 


-0.07502 


-0 . 08354 


-0.08244 


-0.08301 


-0.08842 


-20 . 000 


-0.09137 


-0.08668 


-0.08100 


-0.06921 


-0.06553 


-0 . 06957 


-0.06895 


-0.07249 


-0.07429 


-15.000 


-0.07182 


-0.069m 


-0.05000 


-0 . 05275 


-0.05260 


-0.05437 


-0.05417 


-0 . 05630 


-0 . 05930 


-10.000 


-0 . 04835 


-0. 04 752 


-0.04000 


-0 . 03504 


-0.03800 


-0.03935 


-0.03905 


-0.04081 


-0.04281 


-5.000 


-0.02442 


-0.02417 


-0 . 02000 


-0.02019 


-0.01993 


-0.02165 


-0.02152 


-0.02314 


-0.02395 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01908 


. 02096 


O.01S00 


0.01936 


0.02091 


0.02410 


. 02546 


. 02755 


. 03005 


10.000 


0.03875 


0.04174 


0.03900 


0.03998 


. 04628 


. 04678 


0.05101 


0.05950 


0.06570 


15.000 


0.05817 


0.06023 


. 05S00 


. 06078 


. 06580 


0.07340 


0.08006 


0.09399 


0.10535 


20.000 


0.07S73 


0.07556 


. 07800 


0.06491 


0.09471 


. 1 0376 


O. 11808 


0.13289 


0.14810 



ENGINEER J&C& 
OATZJA-HtIMIZ 



FIGURE 



4.1.1. 

EFFECT 



1-19 

OF ELEVON 



4.1.1.1-24 



* 



Rockwell International 
Space Division 



MACH NUMBER 



3.000 



DELE CDEGD 

-50 -25 



UJ 

CJ 

Q 



i I i I I i < i i I i I I i I I ; i i I I I 



ill 



I I I I 



25 



I I I i 



- k***\ 




TTT 



TTTT 



.6' ' ' I 



I I I I I 



N ii I ii i i h ii 



I I I I ll I I I M I I I 



-20 



-15 



•10 



5 10 

ALPHA CDEG3 



15 



£0 



30 



CONFIGURATION 




BASELINE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW « 78.056 


FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELE (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREf" 


ENT 






-40.000 


-0 . 1 0457 


-0 . oes52 


-0.07000 


-0.06137 


-0.05735 


-0 . 05520 


-0 . 06508 


-0.07535 


-35.000 


-0.09576 


-0.08283 


-0.06000 


-0.05374 


-0.05312 


-0.05873 


-0.05851 


-0.06933 


-30.000 


-0.08796 


-0.06919 


-0.05200 


-0.04709 


-0.04692 


-0 . 05030 


-0.05425 


-0.06186 


-25.000 


-0.07651 


-0 . 06069 


-0 . 04500 


-0 . 04 1 32 


-0.03939 


-0 . 04293 


-0.04955 


-0 . 05440 


-20 . 000 


-0.06210 


-0.05120 


-0 . 03700 


-0.03461 


-0 . 03492 


-0.03439 


-0.04297 


-0.04652 


-15.000 


-0 . 04606 


-0.04081 


-0 . 02700 


-0.02482 


-0.02711 


-0.02S82 


-0.03511 


-0.03S61 


-10.000 


-0.02803 


-0.02742 


-0.01700 


-0.01694 


-0.02039 


-0.02210 


-0.02409 


-0.02579 


-5.000 


-0.01548 


-0.01421 


-0.01000 


-0.01005 


-0.01118 


-0.01299 


-0.01427 


-0.01452 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00916 


. 0C905 


0.00900 


0.01018 


0.01448 


0.01504 


0.01752 


. 02265 


10.000 


0.01535 


0.01992 


0.02=00 


0.02253 


. 02439 


0.03215 


0.04076 


. 04567 


15.000 


0.02215 


. 02464 


. 03400 


0.03708 


. 0450 1 


0.05561 


. 05605 


0.07850 


20.000 


. 02502 


0.03153 


. 04500 


0.05372 


. 06534 


Q.07e62 


. 09333 


0.11012 



ENGINEER OCXl 



FIGURE 



4.1.1.1- 
EFFECT OF 



20 

ELEVON 



4.1.1.1-25 



SD72-SH-0C6C 1 1 VI 



* 



Rockwell International 

Spacs Division 



MACH NUMBER 



CDEG 3 
o 



u 

Q 



-.6 




10 



15 



20 



25 30 
ALPHA CDEGD 



35 



* HO 



45 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO ■ BL 0.0 IN. 

MGtENT REFERENCE ZO = U. 375.0 IN. 



REFERENCE DlfENSIONS 
WING AREA SW - 2590.00 SQ.FT. 
WING SPAN BW « 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB « 1590.3 IN. 



ENG 

DATE 



NEER_D<.0 - 



FIGURE 4.1.1.1-21 

EFFECT OF ELEVGN 





ALPHA CDEG) 




15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELE (OEGJ 


F 


G 


H 


I 


J 


K 


L 






ELEVON NOR 


MAL FORCE I 


NCREf£NT 






-HO. 000 


-0 . 06620 


-0 . 06503 


-0.07635 


-0.09046 


-0.10530 


-0.12130 


-0.13672 


-35.000 


-0 . 05B73 


-0.05S61 


-0 . 06933 


-0 . 08255 


-0 . 09748 


-0.11363 


-0.12952 


-30 . 000 


-0 . 05030 


-0 . 05425 


-0.06186 


-0.07427 


-0 . 08953 


-0.10595 


-0.12126 


-25.000 


-0.04283 


-0.04955 


-0.05440 


-0.06695 


-0 . 08202 


-0 . 09783 


-0.11160 


-20.000 


-0.03*39 


-0.04297 


-0.04652 


-0 . 05903 


-0.07339 


-0.08713 


-0 . 09934 


-15.000 


-0.02S82 


-0.03511 


-0.03561 


-0 . 04677 


-0.05958 


-0 . 07266 


-0 . 08335 


-10.000 


-0.02210 


-0 . 02409 


-0 . 02579 


-0.03352 


-0 . 04233 


-0.05148 


-0 . 05992 


-5.000 


-0.01289 


-0.01427 


-0.01462 


-0.01876 


-0.02270 


-0.02652 


-0.03019 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01604 


0.01752 


0.02265 


0.02819 


0.033G6 


0.03736 


0.03912 


10.000 


0.03215 


0.04076 


0.04567 


0.05937 


0.06961 


0.07775 


0.08338 


15.000 


0.05561 


0.06605 


0.07860 


0.10290 


0.11832 


0.12993 


0.14021 


20.000 


0.07e62 


. 09339 


0.11012 


0.14630 


0.16599 


0.18291 


0.20343 



4.1.1.1-26 



,' (.' '. : 



<1* 



Rockwell International 

Space Division 



J- 



T 



MACH NUMBER 



4. 00f) 



DELE COEG) 

50 -25 25 

nrr 



u 

U 

a 



-.2 



-.4 



I I I I 



-,S< ! I I I I 1 



I 1 I 



-r 



_ r _ .. 







-L_L_L 



I 1 1 I 1 I ' I ! I I I I 



i r r 



-20 -15 -10 -5 5 10 

ALPHA CDEG) 



15 



20 



25 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


Wire AREA S^ - 2SS0.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WINS SPAN BU * 78.055 FT. 


MOrENT REFERENCE ZO = W_ 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH lR » 129G.3 IN. 



ENGINEER £>££> 



FIGURE 



4. 1.1. 1- 

EFFECT OF 



22 

ELEVGN 



30 











ALPHA 


tCEG) 








-10.000 


-5.000 


0.0 


5.0C0 


1 . 000 


15.000 


20.000 


25.000 


DELE (CEO) 


A 


8 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORi'.E 1NCRE1-" 


ENT 






-HO . 000 


-0.09746 


-0.0762! 


-0.05000 


-0.04912 


-0 . 04059 


-0.04540 


-0.05107 


-0.06317 


-35.000 


-0.09178 


-0 . 06849 


-0.05500 


-0.04370 


-0.03766 


-0.04 064 


-0.04673 


-0.05733 


-30.000 


-0.084 14 


-0.06091 


-0.05000 


-0.03915 


-0.03328 


-0 . 03549 


-0.03851 


-0.04957 


-25.000 


-0 . 07385 


-0 . 05346 


-0.04300 


-0 . 03339 


-0 . 02870 


-0.03003 


-0 . 03204 


-0 . 04258 


-20 . 000 


-0.06258 


-0 . 04605 


-0.03600 


-0 . 02863 


-0 . 02595 


-0 . 02429 


-0 . 02700 


-0 . 03579 


-15.000 


-0.05077 


-0 . 03464 


-0 . 02800 


-0 03074 


-0.02013 


-0.01 797 


-0.01957 


-0.02761 


-10.000 


-0.03601 


-0 . 02335 


-0.02000 


-0.01395 


-0 01521 


-0.01269 


-0.01307 


-0. 01930 


-5.000 


-0.02048 


-0.01113 


-0.01200 


-0.CC697 


-0 . 0G823 


-0.0H657 


-0 . 00607 


-0.01072 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00843 


0.00715 


0.00800 


0.01014 


0. 01243 


0.01508 


0.01589 


0.02271 


10.000 


0.01 160 


0.01412 


0.01500 


0.021 u 6 


. 02323 


0.03174 


0.03558 


0.04775 


15.000 


0.01170 


0.01992 


0.02400 


. 03578 


0.04126 


0.05454 


0.06391 


. 08029 


20 . 000 


0.01072 


. 02577 


. 03800 


0.051! 1 


0.0621 1 


. 07826 


. 098 1 a 


0. 1 1629 



4.1.1.1-27 



S D 7 



- S H 



(;Ct. C iM 



4$ 



Rockwell International 

Space Division 



9 



MACH NUMBER 



LU 

8 



.2 



.0 



-.a 



-.4 



4.000 



DELE CDE6D 

-50 -25 25 

| I I I 1 | I I i I |l 1 



i I I | I I I I | II I I | I I 



r tv fe^SjS 






till 



•^v-*^-='^-«v.-=j4is?3r: 



i i i i 



I I I 



n—> — i i i i 




i i i i i i i i 






_L_L 



l l l l 



. ! I IJ. 



I l l l 



I 1 I 



10 



15 



20 



25 

ALPHA 



30 

CDEGD 



35 



40 



45 



50 



CONFIGURATION 




BASELII^ 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - at 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCf€NT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 



ENGINEER 
DATE 








ALPHA (DEG) 


15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELE CDEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVON NOR 


^IAL FORCE I 


NCREMENT 






-40.000 


-0.04540 


-0.05107 


-0.06317 


-0 . 07737 


-0.09172 


-0.10703 


-0.12263 


-35.000 


-0.04064 


-0.04673 


-0 . 05733 


-0.07194 


-0.08756 


-0.10415 


-0.12009 


-30.000 


-0.03549 


-0.03851 


-0 . 04957 


-0.06585 


-0.08086 


-0.CS686 


-0.11230 


-25.000 


-0.03003 


-0.03204 


-0 . 04268 


-0 . 05752 


-0 . 07235 


-0.08816 


-0.10330 


-20 . 000 


-0.02429 


-0.02700 


-0 . 03579 


-0 . 04944 


-0 . 06290 


-0.07715 


-0 . C90S8 


-15.000 


-0.01797 


-0.01957 


-0.02761 


-0.04116 


-0 . 05259 


-0.06481 


-0.07692 


-10.000 


-0.01289 


-0.01307 


-0.01930 


-0 . 03242 


-0 . 03976 


-0 . 04765 


-0.05581 


-5.000 


-0.00657 


-0.00607 


-0.0! 072 


-0.01949 


-0.02371 


-0.02825 


-0 . 03226 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01508 


0.01589 


0.02271 


0.025S5 


0.02975 


0.03384 


. 0364 1 


10.000 


0.03174 


0.03558 


0.04775 


.0.05731 


0.05568 


0.07319 


0.07997 


15.000 


. 05464 


0.05391 


. 08028 


0.09416 


0.10734 


0.11934 


. 1 3002 


20.000 


0.07826 


0.09812 


0.11629 


. 1 3642 


0.15528 


0.17249 


0.18S56 


ZO 


FIC 


,URE 4. 


.1.1-23 











EFFECT OF ELEVON 



4.1.1.1-28 



*i> 



Rockwell International 

Space Division 



u 

a 



















DELt 


: CDEG.i 




MACH NUMBER 


5.000 


-50 -25 C 

! 1 ! 1 | i 1 < 


1 i i 


• t 


4 


1 1 1 1 


1 1 1 I 


till 


III! 


'"V"l 1 ! 


1 1 1 1 


i 1 ' 1 


i ITi 


'iii 


1 1 1 


i 


2 



























- 




:-".VlT.— '■: 




•--r-~e'v-1e 




- — ^-^ 




— -rr 


^X 


— 


~ A^-tc 




^rr^' 1 ^^ 







2 










— 








— 




_ 


4 
R 


1 1 1 1 


1 1 1 1 


1 1 1 1 


1 1 1 1 


1 1 1 1 


Ml! 


! 1 1 i 


ISM 


III! 


L_L_L 


- 



-ao 



-10 



10 



15 



20 



ALPHA CDEGD 



25 



20 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIr€NSIONS 




CENTER Of GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690. CO 


SQ.FT. 


CR YO = BL 0.0 IN. 


WING SPAN BU - 78.056 


FT. 


MOMENT REFERENCE ZO = W_ 375.0 IN. 


M.A.C. CW * 39.560 


FT. 




BODY LENGTH LB = 12S0. 3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


CRCE INCRE^ 


ENT 






-HO. 000 


-0 . 07367 


-0.06043 


-0 . 04500 


-0 . 04022 


-0 . 03398 


-0 . 03874 


-0 . 04492 


-0 . 05733 


-35.000 


-0 . 06599 


-0 . 05370 


-0 . 04500 


-0 . 03677 


-0.03250 


-0 . 03529 


-0 . C4C53 


-0.05.176 


-30 . 000 


-0.05734 


-0.04714 


-0.03800 


-0.C3310 


-0 . 02826 


-0.031 84 


-0.03614 


-0 . 04706 


-25.000 


-0.05015 


-0.04162 


-0.03300 


-0 . 02845 


-0 . 02562 


-0 . 02826 


-0.03154 


-0.04137 


-20 . 000 


-0.042S5 


r-0. 03510 


-0 . 02800 


-0.02471 


-0.02133 


-0 . 02468 


-0.C2535 


-0.03653 


-15.000 


-0.03204 


-0.02671 


-0.02100 


-0.01893 


-0.01726 


-0.01889 


-0.02107 


-0 . 02370 


-10.000 


-0.02506 


-0.01733 


-0.01400 


-0.01304 


-0.01630 


-0.01309 


-0.01895 


-0.0! 335 


-5 . 000 


-0.01336 


-0 . 00905 


-0 . 00700 


-0 . 00602 


-0.00626 


-0 . 00655 


-0.00769 


-0.01105 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00553 


0.00615 


. 00700 


0.00915 


0.01144 


. 1 372 


0.01871 


0.022S6 


10.000 


0.00964 


0.01213 


0.01400 


0.01930 


0.02316 


. 0=764 


. 03325 


0.04357 


15.000 


0.00759 


0.01295 


0.01900 


0.02972 


0.03510 


. 05283 


0.06263 


0.07587 


20 . 000 


. 00265 


. 0.01377 


0.02400 


0.04014 


0.05415 


. 07786 


0.10323 


0. 1 151 ! 



ENGINEER J2<0 



FIGURE 4.1.1.1-24 

EFFECT OF ELEVON 



4.1.1.1-29 



c* 



I c 



Sh"-O n i:C I IV, 



'1* 



Rockwell International 

Spaca Division 



MACH NUMBER 



8 






i i i i m 



\*m 



5.000 
i l I l I I l l I I l I 



DELE CDEG) 

-50 -25 25 



i i ' r 



, s l I M I l-LI i. i 1 i i, i .i. 




I I ! I | I I I 



i i I I 



TTT- 



i I I I 



I- I I M I I I I I I I 



K^*-" 



I 1 I! I I I I I I I 



10 15 20 25 30 35 

ALPHA CDEGD 



HO 45 



50 



55 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN SW - 78.056 FT. 


MOENT REFERENCE 20 » UL 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BCOY LENGTH LB = 1290.3 IN. 





' 






ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (DEG! 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON NORMAL F 


ORCE INCREM 


ENT 






-HO . 000 


-0.0387H 


-0 . 0HH92 


-0 . 05733 


-0 . 07044 


-0 . 06667 


-0.10349 


-0.11889 


-0.13330 


-35.000 


-0.03529 


-0 . 04053 


-0.05176 


-0.06510 


-0.08151 


-0 . 09832 


-0.11442 


-0.12963 


-30 . 000 


-0.031SH 


-0.03614 


-0 . 04706 


-0.05975 


-0 . 07577 


-0.0924H 


-0.10814 


-0.12298 


-25.000 


-0 . 02826 


-0.03154 


-0.04137 


-0.05299 


-0 . 06907 


-0 . 08579 


-0.10087 


-0.11462 


-20 . 000 


-0 . 02H68 


-0.02595 


-0 . 03663 


-0.04709 


-0.06161 


-0.07670 


-0.09047 


-0.10321 


-15.000 


-0.01869 


-0.02107 


-0.02870 


-0 . 03703 


-0 . 04984 


-0.06327 


-0 . 07574 


-0 . 08707 


-10.000 


-0.01309 


-0.01895 


-O.0I9S5 


-0.03038 


-0 . 04074 


-0.05065 


-0.06013 


-0.06901 


-5 . 000 


-0.00655 


-0 . 00759 


-0.01 105 


-0.01751 


-0.02312 


-0 . 02793 


-0.03233 


-0.03647 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01372 


0.01871 


. 02296 


. 02805 


0.03192 


0.03517 


. 03809 


. 0^068 


10.000 


0.0276H 


. 03325 


0.04357 


0.05638 


0.C6512 


. 07257 


0.07954 


0.08570 


15.000 


0.05283 


0.06253 


0.07587 


0.08S59 


0. 10261 


0. 11499 


0.12630 


. 1 3746 


20 . 000 


0.07786 


0.10323 


0.11511 


0.13209 


0. 14776 


0.16355 


0.18226 


0.20429 



ENGINEER £>C£_ 
O^ZjLi-jJ.-lX- 



FIGURE 4.1.1.1-25 

EFFECT OF ELEVON 



4.1.1.1-30 



4% 



Rockwell International 

Space Division 



MACH NUMBER 



8.000 



DELE CDEG'J 
-50 -as 25 



.4 



LU 

-z. 
u 
a 



-.2 



-.4 



-.6 



III. TT 



MM 



I II I 



TT 



Mil' 



TT 



^---%,f=-rc- 7 



I I I 



TTT 



1 I i 



i i 



«**¥** 



Mil 



II II M I l..lj_.l 






I Ml 



_L_L 



J_L 



_L_L 



-20 -15 -10 -5 5 10 

ALPHA CDEGD 



15 



20 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 107S.7 IN. 


WING AREA SU = 2590.00 


SO. FT 


CR YO - BL 0.0 IN. 


WING SPAN BW * 78.056 


FT. 


MOMENT REFERENCE ZO - W_ 375.0 IN. 


M.A.C. CW » 39.550 


FT. 




BODY LENGTH LB = I2S0.3 


IN. 



30 











ALPHA 


(DEG) 








-10.000 


-5.GC0 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (DEG) 


A 


8 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREM 


ENT 






-HO. 000 


-0.07722 


-0.05815 


-0.04200 


-0.03172 


-0.024! 3 


-0 . 02957 


-0.03445 


-0 . 04694 


-35.000 


-0 . 06486 


-0 . 05058 


-0.03700 


-0.03000 


-0.02333 


-0 . 02799 


-0.03298 


-0.04512 


-30 . 000 


-0.05250 


-0.04202 


-0.03300 


-0 . 02729 


-0 . 02365 


-0.02735 


-0.03245 


-0.04245 


-25.000 


-0.04323 


-0.03454 


-0 . 02800 


-0 . 02448 


-0.02179 


-0.02552 


-0 . 02970 


-0.03947 


-20.000 


-0 . 033S5 


-0.02807 


-0.02300 


-0.02167 


-0.019S4 


-0 . 02369 


-0 . 02574 


-0 . 03654 


-15.000 


-0.02487 


-0.02170 


-0.01900 


-0.01778 


-0.01797 


-0 . 02065 


-0 . 02338 


-0.03142 


-10.000 


-0.01580 


-0.01432 


-0.01200 


-0.01488 


-0.01502 


-0.01764 


-0.01962 


-0 . 02630 


-5.000 


-0.00740 


-0.00717 


-0.00700 


-0 . 00SS5 


-0 . 00997 


-0 . 00832 


-0.01239 


-0.01362 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00557 


. 00509 


. 00500 


0.00715 


0.00933 


0.01327 


0.01555 


0.02166 


1 . 000 


. 1 077 


0.01017 


0.01000 


0.01429 


0.01B03 


. 02655 


0.03267 


0.04427 


15.000 


0.01064 


0.01011 


0.01000 


. 02264 


0.02975 


0.C4555 


0.05776 


0.07362 


20 . 000 


0.01224 


0.01105 


0.01100 


0.02999 


. 04662 


. 065^9 


0.03403 


. 1 0=97 



ENGINEER QjZQ. 
DATE ao.-rY-. 7.31 



FIGURE 



4. i. 1.1- 
EFFECT OF 



26 

ELEVON 



4.1.1.1-31 



D7 1 .- -SH-OCUO I; VI 



#1* 



Rockwell Inte national 

Space Division 



MACH NUMBER 



8. 000 



DELE 

■50 -25 

p — r 



UJ 
O 

a 



-.4 



-.6 



TT - 



TTi 



r r p- 



i I i i 



i i i i 



m i r i i i i i 






Mil 



1 ** &3g^~7&^-%r—~\ /-~ 



I I I |-r 



_UL 



^i2%8£ 



i i i 



i i i i 






■l. l I I, 



I I II 



I I I I 




10 15 20 25 30 35 

ALPHA CDEGD 



40 



45 



=50 



5=1 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DI^£NSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU - 2630.00 


SQ.FT. 


OR YO - SL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 38.560 


FT. 




BODY LENGTH L8 - 1290.3 


IN. 











ALPHA 


(OEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


0ELE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEVON NORMAL FORCE INCREMENT 




-40.000 


-0.02957 


-0.03445 


-0.04694 


-0 . 05977 


-0.07577 


-0.09287 


-0.10962 


-0.12641 


-35.000 


-0.02798 


-0.03298 


-0.04512 


-0 . 05667 


-0.07331 


-0 . 09053 


-0.10677 


-0.12220 


-30.000 


-0 . 02735 


-0.03245 


-0.04245 


-0 . 05357 


-0.07030 


-0.08743 


-0.10272 


-0.1 1672 


-25.000 


-0.02552 


-0 . 02970 


-0.03947 


-0 . 0494 1 


-0 . 06485 


-0.08085 


-0.09472 


-0.10695 


-20.000 


-0.02369 


-0.02674 


-0 . 03654 


-0 . 04524 


-0.05879 


-0.07292 


-0.08583 


-0.09775 


-15.000 


-0.02066 


-0.02338 


-0.03142 


-0.03924 


-0 . 05002 


-0.06147 


-0.07282 


-0.08375 


-10.000 


-0.01764 


-0.01962 


-0.02630 


-0.03325 


-0.04013 


-0.04765 


-0.05543 


-0.06322 


-5.000 


-0.00832 


-0.01299 


-0.01362 


-0.02047 


-0.02380 


-0.02761 


-0.03116 


-0.03443 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01327 


0.01555 


0.02166 


0.02669 


0.03080 


0.03396 


C. 03602 


0.03708 


10.000 


0.02555 


0.03267 


0.04427 


0.05586 


0.06499 


0.07197 


0.07662 


0.07965 


15.000 


0.04555 


0.05776 


0.07362 


. 08796 


0.10108 


0.11281 


0.12304 


0.13345 


20 . 000 


0.06549 


0.08403 


. 1 0297 


0.12472 


0.14500 


0.16285 


0.17929 


0.19712 



ENGINEER 
OATEYiL=i£ 



FIGURE 



DS~ 



4.1.1.1 

EFFECT OF 



27 

ELEVGN 



t.1.1. 1-32 



€> 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



DELE CDEG) 

-50 -2S 

i I I I | I I i I I I I 



25 



.0 ■ 



UJ 

z 
u 
Q 



-.2 



-.4 



-.6 



I I II I I I I I 



***! 



I I I I I I 



I II I I I I 



." -c-c.^_ 



I ' i 



illl 



I I I ' I 






TTTT 



I I IT 



I I I I I ! I I I I ) I I I I I I I I I I 



•sj-w^-.*--ii- S&yf-.fri'' 



-20 



-15 



-5 5 10 

ALPHA CDEG) 



15 



20 



25 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 107S.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW « 78.055 


FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 



ENGINEER U>CO 
DATE_.i^5L-Zi?I 



FIGURE 



4. 1. 1.1- 

EFFECT OF 



28 
ELEV0N 



30 











ALPHA 


CDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (DEG^ 


A 


B 


c 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREM 


ENT 






-HO. 000 


-0 . 07889 


-0 . 05933 


-0 . 04200 


-0.03170 


-0 . 02408 


-0 . 02950 


-0.03441 


-0 . 046S4 


-35.000 


-0 . 06632 


-0 . 05070 


-0.03700 


-0.02898 


-0.02331 


-0.02790 


-0 . 03299 


-0 . C4422 


-30.000 


-0.05472 


-0.04308 


-0.03200 


-0.02525 


-0.02154 


-0 . 02630 


-0.03lt8 


-0.04150 


-25.000 


-0 . 04337 


-0.03458 


-0.02800 


-0.02346 


-0.01973 


-0 . 02448 


-0 . 02S65 


-0 . 03852 


-20.000 


-0 . 03203 


-0 . 02708 


-0.02300 


-0 . 02066 


-0.01792 


-0 . 02255 


-0 . 02778 


-0 . 03550 


-15.000 


-0 . 02399 


-0.01972 


-0.01700 


-0.01479 


-0.01400 


-0.01675 


-0 . 02C83 


-0.02S66 


-10.000 


-0.01499 


-0 . 1 336 


-0.01100 


-0.00991 


-0 . 00909 


-0.01179 


-0.01485 


-0.01991 


-5.000 


-0 . 00733 


-0.00618 


-0 . 00500 


-0 . 00495 


-0 . 00503 


-0.00540 


-0 . 00694 


-0 . 00996 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00455 


0.00409 


0.00400 


0.00712 


0.00835 


0.01226 


0.01555 


0.02165 


10.000 


0.00970 


0.00917 


. 00900 


0.01325 


0.01792 


0.02454 


0.03267 


0.04328 


15.0C0 


. 1 072 


0.01010 


0.01000 


. 02062 


0.03275 


. C4450 


0.05776 


. 07259 


20.000 


0.01220 


0.01103 


0.01000 


0.02S99 


0. 04 760 


0.064>*7 


. 08393 


0. ICcBO 



4.1.1.1-33 



SL 



H-OC'.'C J .1 



* 



Rockwell International 

Space Division 



MACH NUMBER 



10. GOO 



DELE CDEGD 

-50 -25 25 

Mil 



LU 
__ 
O 
Q 



I I I | I I I I | i I I I i I I I I I I I 



Til l 




i I l I 



I I I I 






1 I I 1 1 I I I I I I I 






I I I I I I I I 1 I I I I I I I I I I 



^*^¥*" 



i i i 



III! 



r=-M- 



I I I 



10 15 20 25 30 35 

ALPHA CDEG) 



40 45 



50 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 107S.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN ew = 78.056 FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BOOY LENGTH LB - 1290.3 IN. 



ENGINEER g>C_2 
DATEOa.-W.-3i_, 



FIGURE 4.1.1.1-29 

EFFECT OF ELEVCN 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON NORMAL F 


ORCE INCREi- 


ENT 






-40.000 


-0.02950 


-0.03441 


-0 . 04694 


-0.05905 


-0.07587 


-0 . 09370 


-0.11032 


-0.12656 


-35.000 


-0 . 02790 


-0.03298 


-0 . 04422 


-0.05575 


-0.07212 


-0.08929 


-0.10507 


-0.12015 


-30 . 000 


-0 . 02630 


-0.03158 


-0.04150 


-0.05159 


-0 . 06753 


-0 . 084 1 1 


-0 . 09960 


-0. 11430 


-25.000 


-0.02448 


-0 . 02965 


-0 . 03852 


-0 . 0H849 


-0.06319 


-0.07842 


-0.09251 


-0.10574 


-20.000 


-0.02265 


-0.02778 


-0 . 03650 


-0 . 04534 


-0 . 05835 


-0.07196 


-0.08489 


-0.09718 


-15.000 


-0.01675 


-0 . 02C83 


-0.02356 


-0.03583 


-0.04718 


-0.05917 


-0 . 06S98 


-0.07999 


-10.000 


-0.01179 


-0.01485 


-0.01991 


-0.02527 


-0 . 03483 


-0 . 04395 


-0 . 05230 


-0 . 06008 


-5.000 


-0.0C540 


-0 . 00694 


-0.00996 


-0.01491 


-0.01964 


-0 . 02454 


-0.02930 


-0.03391 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01226 


0.01555 


0.02166 


0.02507 


0.02928 


0.03253 


. 03504 


0.03658 


10.000 


0.02454 


. 03267 


0.04328 


0.05489 


0.05385 


0.071 14 


0.07689 


0.08143 


15.000 


. 04450 


. 05776 


0.07259 


0.08760 


. 1 1 06 


0.11259 


0.12251 


0.13204 


20.000 


0.06447 


. 0S393 


. 1 0280 


0.12447 


0. 14471 


0.16246 


0.1787! 


0.19640 



4.1.1.1-34 



#1% 



Rockwell Internations 
Space DrvKion 



MACH NUMBER 

|l, i i l | i I i i i i I i 



15.000 



DELE CDEGD 

-50 -25 25 



I 1 I I 



I I i 



.0 



LU 

z 
(J 

Q 



-.2 



I I I 



I I I I I I I I I I ! I I I I 



, r±-z_—. -r^^^^sdr--~yx— ~^^x 






^6- 



T~T 



I ) ' I 






^'^ 






III! 



I 1 I I 



I I I I 



I i ' I 



-L_J_J_L 



JLI_L_L 






I 1 1 1 I ! I !, ! 



J_L1_L 



-20 



-15 



-10 



5 10 

ALPHA CDEGD 



15 



20 



25 



30 



CONFIGURATION 




BASELINE 0R8ITER 'VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = F5 1076.7 IN. 


WING AREA SW * 2590.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN 8W = 73.055 


FT. 


MOMENT REFERENCE ZO =■ WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BOOY LENGTH LB » 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


CELE <DEG) 


A 


8 


C 





E 


F 


G 


H 






ELEV 


ON NORMAL F 


ORCE INCREM 


_nt 






-HO. 000 


-0.07889 


-0 . 05933 


-0.04200 


-0.03170 


-0.02H08 


-0.02950 


-0.03441 


-0 . 04694 


-35.000 


-0 . 06632 


-0.05070 


-0.03700 


-0 . 02893 


-0.02331 


-0 . 02790 


-0 . 03298 


-0.04H22 


-30 . 000 


-0 . 05472 


-0.0H308 


-0.03200 


-0.02625 


-0.0215H 


-0 . 02630 


-0.03158 


-0.04150 


-25 . 000 


-0. OH 337 


-0 . 03H53 


-0.02800 


-0 . 023H6 


-0.01973 


-0.02448 


-0 . 02965 


-0 . 03852 


-20 . 000 


-0 . 03203 


-0.02708 


-0.02300 


-0 . 02066 


-0.01792 


-0 . 02255 


-0 . 02778 


-0 . 03550 


-15.000 


-0 . 02399 


-0.01972 


-0.01700 


-O.01H79 


-0.01400 


-0.01675 


-0 . 02083 


-0 . 02S66 


-10.000 


-0.01H99 


-0.01335 


-0.01 !00 


-0.00991 


-0.00909 


-0.01179 


-0.01465 


-0.01991 


-5.000 


-0 . 00733 


-0.00618 


-0.00600 


-0 . 00H95 


-0 . 00503 


-0 . 00540 


-0.0C6S4 


-0 . 00996 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00H55 


. 00H09 


0.00H00 


0.00712 


. 00335 


0.01225 


0.01555 


0.02166 


1 . 000 


. 00970 


0.00917 


0.00900 


0.01325 


0.01792 


. 02454 


0.03257 


. 04328 


15.000 


0.01072 


0.01010 


0.01000 


O.C2062 


0.03275 


. 04H50 


0.05776 


. 07259 


20 . 000 


0.01220 


. 1 1 03 


0.01000 


. 02899 


. OH 760 


. 06447 


. 08393 


0. 102S0 



ENGINEER JDCCL 
DATE_.ie_-ry-J2.aI 



FIGURE 



4.1.1. 1- 
EFFECT OF 



30 

ELEVON 



4.1.1.1-35 



SD72-SH-G0G0 I M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



15.000 



DELE CDEG3 

-50 -25 25 

| I I I I | I I I I | I I I I 



.2 



UJ 
8 



-.4 



-.6 



r i i i I i i i i I i 



i i 



r r F - y -**^. J^-z'-J r'ii-- 




I I I ' I I I I I I I I I 



- r! ^ ^^^^~-Js-^--y- 



£-£- 



I ! I I I I I I I 



I I I ! I I I I I I I I 



^?^^r- 



I I I 1 I 1 I 1 I I I I I I 




II' 1 



10 15 20 25 30 35 

ALPHA CDEG) 



HO 



45 



50 



55 



CONFIGURATION 


BASEL !NE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW • 2590.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN 3W - 78.055 FT. 


MOMENT REFERENCE 20 - U_ 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(OEG) 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (DEG) 


F 


G 


H 


1 


J 


K 


L 


M 






ELEV 


ON NORMAL F 


ORCE INCREM 


EXT 






-HO . 000 


-0 . 02S50 


-0.03HH1 


-0.0H69H 


-0 . 05905 


-0 . 07587 


-0.09370 


-0.11032 


-0.12556 


-35.000 


-0 . 02790 


-0.032S8 


-0 . 0HH22 


-0 . 05575 


-0.07212 


-0.08929 


-0 . 1 0507 


-0.12015 


-30 . 000 


-0 . 02630 


-0.03153 


-0. OH 150 


-0.05159 


-0 . 06758 


-0.08411 


-0 . 09960 


-0.11430 


-25.000 


-0 . 02HH8 


-0.02966 


-0.03852 


-0 . 04849 


-0.06319 


-0 . 07842 


-0.09251 


-0.10574 


-20.000 


-0.02265 


-0.02778 


-0 . 03650 


-0 . 04534 


-0 . 05835 


-0.07195 


-0 . 08489 


-0.09718 


-15.000 


-0.01675 


-0.C2083 


-0.02866 


-0.03583 


-0.04718 


-0.05917 


-0 . 06998 


-0 . 07989 


-10.000 


-0.01179 


-0.01485 


-0.01991 


-0 . 02527 


-0.03483 


-0 . 04 395 


-0.05230 


-0 . 06008 


-5.000 


-0.005H0 


-0 . 00694 


-0.00996 


-0.01491 


-0.01964 


-0 . 02454 


-0 . 02930 


-0.03391 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01225 


0.01555 


0.02156 


. 02507 


. 02929 


0.03268 


. 03504 


0.03553 


10.000 


0.02H5H 


. 03267 


0.04328 


. 05489 


0.06385 


0.07114 


. 07669 


0.08143 


15.000 


. 04450 


0.05776 


0.07259 


. 08760 


0.10106 


0.11269 


0.12251 


0.13204 


20.000 


0.06HH7 


0.08393 


0.10290 


0. 12447 


0.14471 


0.16246 


0.17871 


0. 19640 



ENGINEER PC Q 
OATE.iO-A-3/- 



FIGURE 



4.1.1.1- 

EFFECT OF 



31 

ELEVQN 



4.1.1.1-36 



'Jt 



Rockwell International 

Space Division 



J- 



MACH NUMBER 
• H nr~i i i I I i I i I i 



20.000 



DELE CDEG) 

-50 -55 25 

I I I ! | I I I I | I ! I I 



u 

-z. 

o 



-.2 



-.H 



I i I I I I i 



"T 









.-^3&- 



ill 



^ — K 



„*&&-•■& 



-J-- 



I 1 I I I I I I I 1 I I 1 I I I 1 






I I I I 1 1 



i I ! I I I '. I I ! 1 I I 



I ' I 



J 



-20 



•15 -10 -5 5 10 

ALPHA CDEG 3 



15 



20 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER CF GRAVITY XO » F5 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOKENT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BOOY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELE (OEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEV 


ON NORMAL F 


0RCE INCREMi 


:nt 






-40.000 


-0.07869 


-0.05933 


-0.04200 


-0.03170 


-0 . 02409 


-0 . 02950 


-0.03441 


-0 . 04694 


-35.000 


-0 . 06632 


-0 . 05070 


-0.03700 


-0 . 028S9 


-0.02331 


-0 . 02750 


-0.03298 


-0 . 04422 


-3C.0OO 


-0 . 05472 


-0 . 04308 


-0.03200 


-0 . 02625 


-0.02154 


-0 . 02630 


-0.03158 


-0.04150 


-25.000 


-0.04337 


-0 . 03458 


-0.0280C 


-0 . 02346 


-0.01973 


-0 . 02448 


-0 . 02965 


-0.03852 


-20 . 000 


-0 . 03203 


-0 . 02708 


-0.02300 


-0 . 02066 


-0.01792 


-0 . 02265 


-0 . 02778 


-0 . 03650 


-15.000 


-0 . 02399 


-0.01972 


-0.01700 


-0.01479 


-0.01400 


-0.01675 


-0 . 02083 


-0 . 02865 


-10.000 


-0.01499 


-0.01336 


-0.01100 


-0.0099! 


-0 . 00909 


-0.01179 


-0.014S5 


-0.01991 


-5.000 


-0 . 00733 


-O.0OS18 


-0 . 00600 


-0 . 00495 


-0 . 00503 


-0 . 00540 


-0 . 00594 


-0 . 00995 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00455 


. 00409 


0.00400 


0.00712 


0.0C835 


0.01226 


0.01555 


0.02165 


1 . COO 


. 00970 


0.00917 


. 0O9O0 


0.01325 


0.01792 


. 02454 


0.03267 


0.04323 


15.000 


. 1 072 


0.01010 


0.01000 


. 02062 


0.03275 


. 04450 


0.05776 


. 07259 


50.000 


0.01220 


0.01103 


0.01000 


. 02999 


O.C4760 


. 06447 


. 093S3 


0.102e0 



ENGINEER QjCJi 
0ATE_£B.^3L-7JL 



FIGURE 



4. 1.1. 1- 

EFFECT OF 



32 

ELEVON 



4.1.1.1-37 



SL72--oH-OOCO IiVi 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



20.000 



DELE CCEG) 

-50 -25 £5 

f ! I I I | 1 I I I | I > i ! | 




Ll) 

u 

Q 



-.2 



-.6 



I I 1 I I I ! 






I I I I I I I I I I I I I I I I I . I ! I I I I I I I I i -1 



-T+^f^l 



I I i I 



10 15 20 25 30 35 

ALPHA CDEG3 



HO 45 



CONFIGURATION 


BASELINE CR8ITER CHICLE 


REFERENCE DIMENSIONS 


CENTER Cf GRAVITY XO » FS 1075.7 IN. 


WING AREA SW • 2590.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


MOMENT REFERENCE ZO - 14. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 



DELE (DEG) 



-HO . 000 

-35.000 

-30 . 000 

-25.000 

-20 . 000 

-15.000 

-10.000 

-5.000 

0.0 

5. COO 

10.000 

15.000 

20.000 



ALPHA (DEG) 



15.000 

F 



20.000 
G 



25.000 
H 



30.000 
I 



35.000 
J 



40.000 
K 



45.000 

L 



50 . 000 
M 



ELEVON NORMAL FORCE INCREMENT 



-0 . 02S50 
-0.02790 
-0 . 02530 
-0 . 02448 
-0.02265 
-0.01575 
-0.01179 
-0.00540 
0.0 

0.01226 
. 02454 
. 04450 
. 05447 



-0.03441 
-0.032S8 
-0.03158 
-0.02966 
-0 . 02778 
-0 . 02083 
-0.01485 
-0 . 00694 
0.0 

0.01555 
. 03267 
. 05776 
. 08393 



-0 . 04634 
-0.04422 
-0.04150 
-0.03852 
-0 . 03650 
-0 . 02866 
-0.01991 
-0 . 009S6 
0.0 

0.02166 
0.04328 
0.07259 
0.10280 



-0 . 05905 
-0.05575 
-0.05159 
-0 . 04849 
-0 . 04534 
-0.03583 
-0 . 02627 
-0.01491 
0.0 

0.02507 
0.05489 
. C8760 
0.12447 



-0 . 07587 
-0.07212 
-0 . 06758 
-0.06319 
-0 . C5835 
-0.04718 
-0 . 03483 
-0.01954 
.0 

.02923 

.06385 

10106 

14471 



-0 . 09370 
-0.08929 
-0.08411 
-0.07842 
-0.07196 
-0.05917 
-0 . 04395 
-0 . 02454 
0.0 

0.03258 
0.071 14 
0.11269 
0.16246 



-0.11032 
-0.10507 
-0 . 09960 
-0.09251 
-0 . 08489 
-0 . 06398 
-0 . 05230 
-0.02930 
0.0 

0.03504 
0.07689 
0.12251 
0.17871 



-0.12656 
-0.12015 
-0.11430 
-0.10574 
-0.09718 
-0 . 07989 
-0.06003 
-0.03391 
0.0 

0.03658 
0.08143 
0.13204 
0. 19640 



ENGINEER PCO 
PATE_lfl.TK-55_ 



FIGURE 



4. 1. 1. 1- 
EFFECT OF 



33 

ELEVON 



55 



4.1.1.1-38 



'1* 



Rockwell International 

Space Division 



UJ 



a 



-.a 




30 35 

ALPHA CDEG] 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DirENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO « BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOTENT REFERENCE ZO - U_ 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB » 1290.3 IN. 





ALPHA (DEG) 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (OEG) 


A 


8 


C 





E 


F 


G 






ELEVCN NCR 


MAL FORCE 1 


NCREfENT 






-HO- 000 


-0.03441 


-0 . 04694 


-0.05905 


-0 . 07587 


-0.09370 


-0.11032 


-0.12656 


-35.000 


-0.03298 


-0 . 04422 


-0 . 05575 


-0.07212 


-0 . 08929 


-0.10507 


-0.12015 


-30.000 


-0.03158 


-0.04150 


-0.05159 


-0 . 06758 


-0.09411 


-0 . 09960 


-0. 11430 


-25.000 


-0.02966 


-0 . 03852 


-0 . 04649 


-0.06319 


-0.07842 


-0.09251 


-0. 10574 


-20.000 


-0 . 02778 


-0 . 03650 


-0 . 04534 


-0 . 05835 


-0.07196 


-0.08489 


-0.09718 


-15.000 


-0 . 02083 


-0.02866 


-0 . 03533 


-0.04718 


-0.05917 


-0. 05998 


-0.07S39 


-10.000 


-O.0I4S5 


-0.01991 


-0.02627 


-0.03483 


-0 . 04395 


-0.05230 


-0.06008 


-5.000 


-0.006S4 


-0.00995 


-0.01491 


-0.01S64 


-0 . 02454 


-0.02930 


-0.03391 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01555 


0.021S6 


. 02507 


0.02928 


0.03268 


. 03504 


. 03658 


10.000 


0.03267 


0.04328 


0.05489 


. C6385 


0.07114 


0.07639 


0.08143 


15.000 


0.05776 


. 07259 


0.08760 


0.10106 


0.11269 


0.12251 


0. 13204 


20.000 


. 0B393 


0.10280 


0. 12447 


0. 14471 


0.16246 


0.17871 


0.1S&-0 



ENGINEER NASA 
DATE ~~Z~ 



FIGURE 



4. 1. 1. 

EFFECT 



1-34 

OF ELEVCN 



4.1.1.1-39 






■ '_; r\ r 

~ .. r i - u v. 



\1 



€* 



Rockweil International 
Space Division 



]__ 



DELE CDEGD 

50 -25 

M I I | I | I I 



UJ 

u 
a 




30 35 

ALPHA CDEG) 



CONFIGURATION 




BASELINE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


UING AREA SW = 2690.00 


SQ.FT. 


OR YD ' BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BOOY LENGTH LB = 1290.3 


IN. 



C€LE (OEG) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20 . 000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20 . 000 



20.000 
A 



ALPHA (OEG) 



25.000 
8 



30 . 000 
C 



35.000 
D 



40.000 
E 



45.000 

F 



50 . 000 
G 



-0.03441 
-0.03298 
-0.0315B 
-0.02966 
-0.02778 
-0.02083 
-0.01485 
-0.00694 
0.0 

0.01555 
0.03267 
0.05776 
. 08393 



ELEVON NORMAL FORCE INCREMENT 



-0 

-0 
-0. 
-0. 
-0 
-0 
-0. 
-0, 

0. 

0. 

o. 

0. 

0. 



04694 

04422 

04150 

03852 

03650 

02S56 

01991 

00996 



02156 

04328 

07259 

10280 



ENGINEER 
DATE ! 



NASA 



FIGURE 



-o, 

-0. 
-0. 
-0, 
-0, 
-0. 
-0. 
-0. 

0. 

0. 

0. 

0. 

0. 



05905 

05575 

05159 

04849 

04534 

03583 

02627 

01491 



02507 

05489 

08760 

12447 



-0.07587 
-0.07212 
-0.06758 
-0.06319 
-0.05835 
-0.04718 
-0.03483 
-0.01964 
0.0 

0.02928 
0.06385 
0.10106 
0. 14471 



-0.09370 
-0.08929 
-0 . 084 1 1 
-0 . 07842 
-0.07196 
-0.05917 
-0 . 04395 
-0.02454 
0.0 

0.03263 
0.07114 
0.11269 
0.16246 



-0.11032 
-0.10507 
-0.09950 
-0.09251 
-0 . 08489 
-0 . 06998 
-0.05230 
-0 . 02930 
0.0 

0.03504 
0.07689 
0.12251 
0.17871 



-0.12656 
-0.12015 
-0.11430 
-0.10574 
-0.09718 
-0.07989 
-0.06008 
-0.03391 
0.0 

0.03658 
0.08143 
0.13204 
0.19540 



4.1. 1. 
EFFECT 



1-35 

OF ELEVGN 



4.1.1.1-40 



'J* 



Rockwell International 

Space Division 



ALTITUDE CFT.) = 300,000 to 600,000 

•2|' i i i m i I'M I I I I I I i 



DELE CCEG) 

-25 



o 

a 



.0 



-. i 



i ,i i l 



i i i l 



„LJ_J_L 




- r^^i-^ 



_l 



■ii i 



w~ 



Ll. 



I I I I 



10 



15 



20 



30 35 

ALPHA CDEGD 



40 



45 



50 











CONFIGURATION 












BASELINE 0RB1TER 


VEHICLE 






REFERENCE 


DIMENSIONS 






CENTER 


OF GRAVITY 


XO 


* FS 


107S 


7 


IN. 


WING 


AREA 


SW » 


3690 . 00 


SO.. 


FT. 




OR 


YO 


- BL 








IN. 


WING 


SPAN 


BW = 


78.055 


FT. 




M0CENT 


REFERENCE 


zo 


» U. 


375 





IN. 


M.A.C. 


CW = 


39.550 


FT. 


















BCOY 


LENGTH 


LB » 


1290.3 


IN. 







ALPHA (OEG) 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50.000 


DELE (DEG) 


A 


9 


C 





E 


F 


G 






ELEVON NOR 


MAL FORCE ! 


CEMENT 






-HO . 000 


-0.03441 


-0 . 04634 


-0.05905 


-0.07587 


-0.09370 


-0.11032 


-0.12656 


-35.000 


-0 . 03298 


-0 . 04422 


-0 . 05575 


-0.07212 


-0-08929 


-0.10507 


-0.12015 


-30 . 000 


-0.03158 


-0.04150 


-0.05159 


-0 . 06758 


-0 . 084 1 1 


-0 . 09950 


-0.11430 


-25.000 


-0 . 02SS6 


-0 . 03852 


-0.04849 


-0.06319 


-0 . 07842 


-0.09251 


-0.10574 


-20 . 000 


-0.02778 


-0 . 03550 


-0.04534 


-0 . 05835 


-0.07196 


-0 . 08489 


-0.09718 


-15.000 


-0 . 02083 


-0 . 02665 


-0 . 03583 


-0.04718 


-0.05917 


-0 . 06998 


-0 . 07989 


-10.000 


-0.01485 


-0.01991 


-0.02627 


-0 . 03483 


-0.C4395 


-0 . 05230 


-0 . 06008 


-5.000 


-0.00694 


-0.00996 


-0.01491 


-0.01964 


-0 . 02454 


-0.02930 


-0 . 0339 1 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01555 


0.02166 


. 02507 


0.02928 


0.03268 


0.03504 


. 03658 


10.000 


0.032S7 


0.04328 


0.05489 


0.06385 


0.07114 


0.07689 


0.08143 


15.000 


. 05776 


. 07259 


. 08760 


0.10106 


0.11269 


0.12251 


0. 13204 


20.000 


. 08393 


0. 10280 


0.12447 


0. 14471 


0. 16246 


0. 1787! 


0. 1S540 



ENGINEER N AS A_ 
DATE I__I 



FIGURE 



4. 1. 1. 

EFFECT 



1-36 

OF ELEVON 



k.l.l.l-Ul 



SD72-SH-0CCC I 



'1* 



Rockwell International 

Space) DMbmo 



UJ 

en 

z 



i.o 



0.8 



o.s 



0.4 



0.2 




2.0 2.5 

MACH NUMBER 



4.0 











CONFIGURATION 










BASELINE ORBITER 


VEHICLE 






REFERENCE 


DIMENSIONS 






CENTER 


OF GRAVITY 


XO 


- PS 


1076 


7 


IN. 


WING AREA 


SW = 


2690 . 00 


SO. 


FT. 




CR 


YO 


- BL 








IN. 


WING SPAN 


ew » 


78.055 


FT. 




MGtCNT 


REFERENCE 


20 


' A. 


375 





IN. 


M.A.C. 
BODY LENGTH 


cw - 

LB - 


39.560 
1230.3 


FT. 
]N. 







DELE (OEG) 




-5.000 


0.0 


5.000 


HACH Nl*«ER 


A 


a 


C 


NCPHAL fCRC 


£ PARTIAL S 


Pan "actcr 


0.250 


0.50000 


0.60000 


O.SOOOO 


0.400 


0.50000 


0.60000 


0.5COOO 


o.soo 


0.50000 


0.60000 


0.50000 


0.800 


0.69000 


0.65000 


0.58000 


0.900 


0.80000 


0.73000 


0.570C0 


0.950 


0.83000 


0.76000 


0.58000 


0.980 


0.84000 


0.77000 


0.59000 


1.050 


O.S4000 


0.7S0C0 


0.51000 


1.100 


0.83000 


0.77=00 


0.S2000 


1.200 


o.aoooo 


0.75000 


0.63000 


1.300 


0.75000 


0.70000 


0.52000 


1.500 


0.6S0O0 


O.S3000 


O.6G00O 


2.000 


0.60000 


0.50000 


. 60000 


3.000 


0.50000 


0.50000 


O.SOOOO 


4.000 


0.50000 


0.60000 


0.50000 


5.000 


0.60000 


0.60C00 


0.60000 


3.000 


0.60000 


0.60000 


0.50000 


10.000 


0.60000 


0.50000 


O.SOOOO 


15.000 


0.60000 


0.60000 


0.50000 


20.000 


0.60000 


O.SOOOO 


0.5C000 



NOTE: In the event par; ill 
span 'actors are 
required wnich excteo 
trie ji van 1 imi ts, tn« 
Aero Data Uni c at 
Rockwall Internaclon' I 
should io contacted 
ztfort extraoolatlon 
of the given 4aca. 



ENGINEER UJWL. 
OATE va -_t JO * 



&//-U-T? 



FIGURE 4.1.1.1-37 

ELEVCN PARTIAL SPAN FACTCR 



4.1.1.1-42 



<i* 



Rockwell International 

Space Division 



MACH NUMBER 



0.250 



OELBF CDEG) 

25 25 



CO 
U 

a 



~i 




5 10 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XC =» FS 1076.7 IN. 


WING AREA SU = 2590.00 SQ.FT. 


CR YO = BL 0.0 IN. 


WING SPAN 3W » 78.056 FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BCCY LENGTH LB - 1290.3 IN. 











ALPHA 


COEG1 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELBF (DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCRE 


^£NT 






-11.700 


-0. 03407 


-0.03291 


-0 . 03220 


-0.03187 


-0.03180 


-0.03109 


-0 . 03005 


-0.02693 


-5.000 


-0.01430 


-0.01393 


-0.01379 


-0.01372 


-0.01376 


-0 . 1 365 


-0.01 346 


-0.01312 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01349 


0.01382 


0.01380 


0.01382 


0.01396 


0.014C9 


0.01426 


0.0141 1 


10.000 


0.02692 


0.02752 


0.02761 


0.02774 


0.02912 


0.02866 


0.02938 


0.02927 


16.300 


. 04392 


. 04474 


0.04520 


. 04567 


. 04663 


0.04815 


0.05017 


0.05047 


22.500 


. 0.077S0 


. 0780 1 


0.07780 


0.07770 


0.07782 


0.07719 


. 07762 


0.07S6! 



ENGIf>£ER UirtiT- 

oate rXrXC-J? * 



FIGURE 4.1.1.1-38 
EFFECT GF "BCDY FLAP 



4.1.1.1-43 



SD 



SH-CC6C 1M 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 
10 ' i i I I I i I I I I i 



0.400 



DELBF CDEG) 

-25 E5 

I i i i i I i r~r ,_ n 



lo- 
CO 

-z. 
(_) 
a 



.09 



.06 



.04 



.02 



.0 



-.02 



.04 



i I I I 



I I I l 



■15 




I I I | I I I l 



CONFIGURATION 


BASEL INE ORB ITER VEHICLE 


REFERENCE D I. -ENS IONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MCNENT REFERENCE 20 - U. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCRE 


^ENT 






-11.700 


-0.03407 


-0.03291 


-0.03220 


-0.03187 


-0.03180 


-0.03109 


-0 . 03005 


-0 . 02893 


-5.000 


-0.01430 


-0.0139a 


-0.01379 


-0.01372 


-0.01375 


-0.01365 


-0.01346 


-0.01312 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01349 


0.01382 


0.01380 


0.01382 


0.013S6 


0.01409 


0.01425 


0.0141 1 


10.000 


0.02592 


0.02752 


0.02761 


0.02774 


0.02812 


0.02866 


0.02938 


. 02927 


16.300 


0.04392 


0.04474 


. 04520 


. 04567 


0.04663 


0.04815 


0.05017 


. 05047 


22.500 


. 07780 


0.07801 


0.07780 


. 07770 


. 07782 


0.07719 


0.07752 


0.07S6I 



ENGINEER (<y>n^ 
DATE. "±tLl-7S 



FIGURE 4.1.1.1-39 

EFFECT OF BODY FLAP 



4.1.1.1-44 



#J> 



Rockwell International 

Spaca Division 



1- 



MACH NUMBER 



0.S00 



CD 

u 

Q 



.10 



.08 



.06 



.OH 



.02 



.02 



.04 



I I I 



i L 1. 



-LI I ,1 



I I I I 



III) 



ill! 



i i i r 




i i i 



CELBF CDEGD 

-25 25 

I i i > i I i i i i ; 

in - )— i 



i i i i 



JIM 



i I I I. 



I Hi 



— -fl 



H-Z7z__y 



i i i i 



i i i i 



i : i 



-15 



-10 



-5 



5 10 

ALPHA CDEG) 



20 



25 



30 



CONF IGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 25S0.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELBF (DEG) 


A 


B 


C 





E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCREMENT 






-11.700 


-0.02116 


-0.02050 


-0.02267 


-0.02361 


-0.02434 


-0.02661 


-0.02818 


-0.02980 


-5.000 


-0.01 078 


-0.01058 


-0.01112 


-0.01142 


-0.01171 


-0.01258 


-0 . C 1 325 


-0.01395 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01550 


0.01525 


0.01455 


. 1 363 


0.01458 


0.01481 


0.01589 


0.01629 


10.000 


0.03210 


0.03201 


0.03053 


0.02S25 


. 03068 


0.03133 


0.03316 


. 03426 


16.300 


0.05318 


. 05332 


0.05111 


0.05112 


0.05181 


' 0.05347 


0.C5578 


. 0580S 


22.500 


0.07416 


. 07446 


0.07182 


0.07484 


0.07345 


0.07651 


. 07884 


O.0S2SI 



ENGINEER U>Ml 
DATE ZZfL^iJr")« 



FIGURE 4.1.1.1-40 

EFFECT GF BODY FLAP 



4.1.1.1-45 



sc 



SH-f"!~C iM 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



0.80C 



CD 

U 
Q 



.10 



.08 



.06 



.cm 



.02 



.0 



-.02 



-.04 



DELBF CDE6) 
-25 £5 



i i i i 



i i i 



-15 




1-^-4- 



5 10 

ALPHA CDEGO 



CONFIGURATION 


BASELINE 0R9ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO = 8L 0.0 IN. 


WING SPAN BW => 78.056 FT. 


MCr-ENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BOOY LENGTH LB • 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (OEG) 


A 


B 


C 





E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE INCRE 


^£NT 






-11.700 


-0.02634 


-0.02561 


-0.02630 


-0 . 02784 


-0.02783 


-0 . C2522 


-0.03033 


-0.03051 


-5.000 


-0.01240 


-0.01220 


-0.01238 


-0.01294 


-0.01321 


-0.01302 


-0.01462 


-0.01495 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01502 


0.01528 


0.01515 


0.01481 


0.01562 


0.01687 


0.01817 


0.01917 


10.000 


0.03135 


0.03176 


0.03139 


0.03116 


0.03313 


. 03595 


. 03835 


. 04059 


16.300 


0.05231 


0.05273 


0.05215 


. 05308 


0.05672 


0.06128 


. 06485 


0.06856 


22.500 


0.07336 


. 07358 


0.07291 


0.07592 


0.08142 


. 08743 


0.C9I93 


. 09702 



ENGINEER luwI. 
DATE II5H5I=">* 



FIGURE 4.1.1.1-U 
EFFECT OF BODY FLAP 



4.1.1.1-46 



#J* 



Rockwell International 

Space Drvskxi 



MACH NUM8ER 



DELBF CDEG) 

25 25 



n 



Ll. 
OQ 

z 
<_> 
a 




.04 ' I I 1 I 
-15 -10 



10 

CDEG 3 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1075.7 IN. 


WING AREA SW = 5690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 73.056 FT. 


MC*-£NT REFERENCE ZO « WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCPE 


-ENT 






-11.700 


-0.02099 


-0 . 02027 


-0.01973 


-0.01710 


-0.01863 


-0.01B98 


-0.C20I6 


-0.02332 


-5.000 


-0.01147 


-0.01C96 


-0.01009 


-0.00917 


-0.01013 


-0.01100 


-0 . 1 1 75 


-0.01313 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01B51 


0.01732 


0.01478 


0.01466 


0.01440 


0.01772 


. 02093 


. 0225C 


10.000 


. 03970 


0.03618 


0.03100 


0.02981 


0.03172 


. 03853 


0.04301 


. 04623 


16.300 


0.06337 


0.05819 


0.05010 


0.04918 


. 05552 


. 065S6 


. 07092 


. 07563 


22.500 


. 08272 


. 07789 


0.06731 


0.06356 


. 08085 


. 09390 


o . o°eeo 


0. 10414 



ENCIPHER Ui>V>3_ 
OATE„-__~3_«_3.J--)t 



FIGURE 4.1.1.1-42 

EFFECT OF BODY FLAP 



C 



4.1.1.1-47 



'S D 7 ?- - S H - C c C i M 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



0.950 



DELBF CDEG) 

25 25 

I I I I | I 



u. 

00 

u 
a 




CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO =» FS 1076.7 IN. 

OR YO = BL 0.0 IN. 

MCf-tNT REFERENCE ZO =" WL 375.0 IN. 



REFERENCE DireNSIONS 
WING AREA SW - 2590.00 SQ.FT. 
WING SPAN SJ » 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 











ALPHA 


COEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (OEG1 


A 


B 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCRE 


l-ENT 






-11.700 


-0.02670 


-0 . 02506 


-0 . 02072 


-0.01660 


-0.01627 


-0.01957 


-0.02460 


-0 . 02773 


-5.000 


-0.01247 


-0.01193 


-0.01036 


-0.00831 


-0 . 00820 


-0 . 00959 


-0.01139 


-0.01257 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01512 


0.01516 


0.01420 


0.01143 


0.01059 


0.011 19 


0.01245 


0.01340 


10.000 


0.03129 


0.0312! 


. 02953 


. C2374 


0.02284 


0.02406 


0.02598 


0.02761 


16.300 


0.05173 


0. 05154 


0.04934 


. 03955 


0.03961 


0.04352 


0.04614 


0.04S51 


22.500 


0.071S9 


0.07171 


. 06905 


0.05581 


0.05748 


0.06675 


0.07194 


. 07702 



EnGIn££R 1,^1. 
DATE I"5--"3J -1 8 



FIGURE 4.1.1.1-43 

EFFECT GF BODY FLAP 



4.1.1.1-48 



a 



Rockwell International 

Spec* Division 



MACH NUMBER 



DELBF 



CDEG.i 

25 



Ll 
CD 

o 




CONF 1GURATI0N 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO * FS 1076.7 IN. 

OR YO ' BL 0.0 IN. 

MGfENT REFERENCE ZO = U_ 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
UING SPAN BW = 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BOOY LENGTH LB -1290.3 IN. 









— — *" 


ALPHA 


(DEG) 









-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCPE 


h£NT 






-11 .700 


-0.02508 


-0.02377 


-0.019S8 


-0.01654 


-0.01625 


-0.01975 


-0 . 02488 


-0 . 02754 


-5.0C0 


-0.01149 


-0.01122 


-0 . 00994 


-0.00810 


-0 . 00803 


-0.00921 


-0.01103 


-0.01202 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01264 


0.01341 


0.01316 


0.01015 


0.01058 


0.01025 


0.01 155 


0.01222 


10.000 


0.02543 


0.02816 


. 02787 


0.02157 


. 02278 


0.02159 


. 02365 


. 02453 


16.300 


. 04535 


0.04744 


. 04698 


0.03712 


0.03750 


. 03306 


0.039S9 


Q . 04 1 79 


22.500 


0.06561 


. 06705 


. 06535 


0.05324 


0.05051 


0.05715 


0.06229 


. 0575 1 - 



ENGINEER lv**1- 
OATE I"??I?I-">3 



FIGURE 4.1.1.1-44 

EFFECT OF BODY FLAP 



4.1.1.1-49 



SD7--SH CCCC :M 



4* 



Rockweli international 
Space Division 



MACH NUMBER 



OELBF CDEG) 

-25 25 



CD 

-z. 
o 

Q 




5 10 

ALPHA CDEG) 



30 



CONFIGURATION 



BASELINE CRBITER VEHICLE 

CENTER OF GRAVITY XO « F5 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCtCNT REFERENCE ZO =• U. 375.0 IN. 



REFERENCE 01 PENSIONS 
U'NG AREA SA = 2690.00 SQ.FT. 
WING SPAN BW = 78.055 FT. 
M.A.C. CW - 39.550 FT. 

BODY LENGTH 13 - 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCRE 


"CUT 






-11.700 


-0.0 1422 


-0.01476 


-0.01613 


-0.01704 


-0.01975 


-0.01971 


-0.02134 


-0.02337 


-5 . 000 


-0.00701 


-0.00756 


-0 . 00802 


-0.00814 


-0 . 00S20 


-0.00895 


-0.00977 


-0.01031 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00810 


0.01021 


0.01054 


. 00960 


0.01093 


. 00993 


0.01023 


0.01C52 


10.000 


0.01752 


0.C21S9 


. 02236 


. 02047 


0.02328 


. 02075 


0.02115 


0.02137 


16.300 


0.03255 


0.03753 


0.03776 


. 03545 


0.03793 


0.03478 


. 035S5 


. 03590 


22.5C0 


0.05150 


. 05348 


0.05340 


0.05145 


0.04717 


0.04752 


0.05125 


0.05513 



ENGINEER U^mZ. 
DATE "I5?ZU-7g 



FIGURE 4.1.1.1-^5 

EFFECT OF BODY FLAP 



4.1.1.1-50 



4% 



Rockwell International 

Space OrvtsJofi 



MACH NUMBER 



1. 100 



DELBF CCEG) 

-25 25 

i i i i I i r 



00 

Z 

u 

a 




CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW ' 2690.00 SQ.FT. 
WING SPAN BW = 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1890.3 IN. 











ALPHA 


(DEG) 









-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE INCRE 


-ENT 






-11.700 


-0 . 00935 


-0.01070 


-0.01427 


-0.01705 


-0.02040 


-0.01908 


-0.01901 


-0.01936 


-5.000 


-0.00504 


-0 . 0C573 


-0 . 00705 


-0.00810 


-0.00943 


-0.00863 


-0.0C865 


-0 . 00882 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00634 


0.00778 


0.00894 


0.00949 


0.01120 


0.00949 


. 00957 


. 00965 


10.000 


0.01425 


0.01726 


0.01918 


0.02016 


0.02349 


0.01968 


0.01998 


0.02014 


16.300 


0.02723 


0.03071 


0.03286 


0.03484 


0.03809 


. 03307 


0.03357 


0.03449 


22.500 


0.04362 


. 04536 


0.04705 


0.05051 


0.04764 


0.04363 


. 04666 


0.0^983 



ENGINEER Ujywj,. 



FIGURE 4.1.1.1-46 
EFFECT OF BODY FLAP 



4.1.1.1-51 



SD 



71-SH-CCCC !M 



* 



Rockwell International 

Space Division 



MACH NUMBER 
l0 M I I 



1.200 



DELBF CDEG) 

-25 25 

I I I I I I I > i i 



CO 
2T 

O 

o 



.08 



.06 



.04 



.03 



-.02 



.04 



1111 



IT 



111! 



T 



MM 




M f T 






I 1 I I 



I I L 



_L 



I I i i 



-L.J L 



i i rn r 




MM 



l l I I 



! I ! 



-15 



-10 



-5 



5 

ALPHA 



10 

CDEG) 



15 



20 



25 



30 



CONFIGURATION 


BASELINE CR8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2590.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW » 78.055 FT. 


MOMENT REFERENCE ZO « WL 375.0 IN.' 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB « 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 


H 






BCDYF 


LAP NORMAL 


FORCE INCRE 


MENT 






-11 .700 


-0.00S92 


-0.0101 1 


-0.01352 


-0.01503 


-0.01125 


-0.01209 


-0.01128 


-0.00906 


-5.000 


-0.00503 


-0.0C550 


-0.0C659 


-0.00745 


-0.00643 


-0 . 00622 


-0 . 00598 


-0.00533 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.007SO 


. 00872 


0.00775 


0.00968 


0.01006 


0.00852 


. 0C834 


0.00831 


10.000 


0.01716 


0.01819 


0.01669 


. 02060 


0.02199 


0.01875 


0.01834 


0.01851 


16.300 


. 02902 


0.03020 


0.02986 


0.03491 


. 03760 


0.03120 


0.03140 


. 03243 


22.500 


0.04078 


0.04217 


0.04500 


. 04954 


0.05409 


0.04183 


0.04435 


. 04724 



DATE. 



.zrifexi- 



"58 



FIGURE 4.1.1.1-47 

EFFECT OF BODY FLAP 



4.1.1.1-52 



*i* 



Rockwell International 

Space CivNtcn 



MACH 



u. 

GO 

-z. 
u 

Q 



NUMBER 
I I l I 



DELGF COEG) 

25 25 

i I I I 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO * BL 0.0 IN. 

MOfENT REFERENCE ZO » WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB = 1230.3 IN. 



r 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20. GOO 


25.000 


OELBF (OEG) 


A 


B 


C 





E 


F 


G 


H 






BOOYF 


LAP NORMAL 


FORCE INCRE 


-£NT 






-11.700 


-o.ao6m 


-0.00725 


-0 . 0094 1 


-0.01090 


-0.01175 


-0.01278 


-0.01264 


-0 . 1 34 1 


-5.000 


-0 . 00378 


-0 . 00423 


-0.00505 


-0.00593 


-0 . 00654 


-0.00685 


-0 . 00658 


-0.006S5 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00708 


0.00766 


. 0082B 


0.00919 


. 1 056 


0.01C52 


. 1 004 


0.01023 


10.000 


0.01469 


0.015S8 


0.01669 


. 02008 


0.02312 


0.02313 


. 02079 


0.02l u 8 


16.300 


. 02427 


0.02550 


0.02718 


0.03247 


0.03699 


0.03634 


. 03367 


0.03534 


22.500 


. 03377 


0.03423 


0.C3740 


. 04250 


0.0470! 


. 04425 


. 04554 


0.04863 



ENGINEER 
DATE ; 






FIGURE 4.1.1.1-48 

EFFECT OF BODY FLAP 



4.1.1.1-53 






SD7 



S H - c c (-: C I M 



#1* 



Rockwell International 

Spaca Division 



li- 
Z 

u 
a 



MACH NUMBER 



1.500 



DELBF CDEG) 

-25 25 



10 



.08 



.05 



.OH 



.02 



.0 



.02 



-.04 



I I I 



1 1 1 .1 



TTTT 




i-l-J-L 



i I I i 



| I t I I 



AZZ^T^ 



III! 



Ei?£ 



i i i i 



.i._j_. 



TT 



I I 1 



i I I I 




II I TH IT 



I I I I 



i I ! I 



' I I I I I I I i 



■15 



-10 



-5 



5 

ALPHA 



10 

CDEGD 



15 



20 



30 



COM 7 1 CURAT ION 


BASEL I NE ORB ITER VEHICLE 


REFERENCE 01 PENSIONS 


CENTER OF GRAVITY XO * FS 1076.7 IN. 


WING AREA SW = 2590.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


MOTCNT REFERENCE ZO « UL 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BOOY LENGTH LB = 1290.3 IN. 











" ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF <DEG) 


A 


8 


C 





E 


F 


G 


H 






6CCYF 


LAP NORMAL 


FORCE INCREI 


htNT 






-11.700 


-0.01002 


-0.01069 


-0.01019 


-0 . 00956 


-0.01057 


-0.01300 


-0.01383 


-0.01330 


-5.000 


-0 . 00456 


-0 . 00468 


-0.00484 


-0 . 00504 


-0 . 00550 


-0 . 00646 


-0 . 00685 


-0.00699 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00528 


0.00568 


. 00604 


. 00744 


0.00833 


. 00893 


. 00955 


0.01055 


10.000 


0.01103 


0.01 192 


0.01297 


0.01657 


0.01854 


0.01889 


0.01995 


0.02257 


16.300 


0.01773 


0.01904 


0.02077 


0.02528 


0.02952 


0.03033 


0.03217 


0.03625 


22.500 


. 02343 


0.02452 


. 02633 


0.03106 


0.03383 


. 03838 


0.04120 


. 04632 



ENGINEER <*>**%. 

date. ~g[:lL-"»* 



FIGURE 4.1.1.1-49 

EFFECT OF BODY FLAP 



4.1.1.1-54 



0& 



Rockwell International 

Space Division 



CO 



MACH NUMBER = 2.000 

1Q « I I I I I I ! M I I I I I | i I I I I I I I I 



OELBF CDF.G) 

-25 £5 

TTTTTTTT] 



.08 



.06 



.04 



.02 



.02 



n=)r-±^"&&&~. 



Q., 11 I i i 1 I t i i. I 1 I i I 



i M i 




T I ! I I I I 



1 I I I I I I i I 



I I... I. I I I I I l I l I l 



■15 



■10 



-5 



5 10 15 

ALPHA CDEGD 



20 



.1 I I I l I 1 I I 1 .1 
25 30 



35 



CONFIGURATION 


BASEL INE ORBITER VEHICLE 


REFERENCE DI^NSIONS 


CENTER OF GRAVITY XO - FS 107B.7 IN. 


WING AREA SW « 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


UING SPAN BW - 78.056 FT. 


MCt-ENT REFERENCE ZO = W. 375.0 IN. 


M.A.C. CUI =■ 39.560 FT. 




BODY LENGTH LB » 1290.3 IN. 



1 





ALPHA (OEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30 . 000 


CGL8F IDEG) 


A 


B 


C 


D 


£ 


F 


G 


H 


I 








80DYFLAP NORMAL FORCE 


INCREMENT 








-11.700 


-0.00197 


-0 . 00299 


-0.00439 


-0 . 00722 


-0 . 00960 


-0.01213 


-0.01427 


-0.01495 


-0.01541 


-5.000 


-0.00158 


-0.00198 


-0.00249 


-0.00354 


-0.00446 


-0 . 00545 


-0.00640 


-0 . 00685 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00364 


0.00391 


. 00429 


0.00464 


. 00532 


. 00598 


0.00694 


0.00765 


0.00797 


10.000 


0.00799 


. 00863 


0.00891 


0.00999 


0.01107 


0.01248 


0.01444 


0.01600 


0.01675 


16.300 
22.500 


0.01280 


0.01377 


0.01444 


0.01613 


0.01818 


0.02051 


0.02392 


0.02706 


. 03005 


0.0I67M 


. 1 767 


0.01958 


. 02094 


0.02491 


0.02688 


. 03204 


0.03948 


0.04571 



ENGINEER C**nT, 

date :£-zn-5s 



FIGURE 4.1-1. t-50 

EFFECT OF BCOY FLAP 



4.1.1.1-55 



SL72-SH-OCCC 1M 



€> 



Rockwell International 

Space Division 



MACH NUMBER 
■ 10 <-i l I I I l l I 



CQ 
J 

o 



.08 



.06 



.04 



.02 



.02 



-.OH 



A A - ? 



J_L 



3.000 



DELBF CDEGD 

-25 25 

| I I I I 






I. I I . 1 , 



I I I i 



III! 



I I i I 



I I I I 




J_L 



! I I | I I I 



I I I 



I I I 



I I I 



I I I I 



I I, ,1. I. 



-15 



■10 



-5 



5 
ALPHA 



10 

CDEG3 



15 



20 



25 



30 



CONFIGURATION 




BASELINE 0R81TER VEHICLE 


REFERENCE ON-tNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW * 2690.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - HL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH L8 - 1290.3 


IN. 









■ 


ALPHA 


(DEC) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (C€G) 


A 


8 


C 


D 


E 


F 


G 


H 






BODYF 


LAP NORMAL 


FORCE INCRE 


MENT 






-11.700 


-0 . 00043 


-0.00175 


-0 . 00222 


-0.00378 


-0 . 00500 


-0.00553 


-0 . 00855 


-0.01110 


-5.000 


-0 . 00045 


-0.00097 


-0.00124 


-0.00191 


-0.00252 


-0 . 00330 


-0.00421 


-0.00534 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00081 


0.00135 


0.00169 


. 00265 


0.00344 


0.00456 


. 00567 


. 00552 


10.000 


0.001S8 


. 00302 


0.00381 


. 00557 


. 00727 


0.009S8 


0.01168 


0.01385 


16.300 


0.0039H 


. 00544 


. 00707 


0.00931 


0.01223 


0.01607 


0.01942 


0.02361 


22 . 500 


0.006^0 


o . ooeoH 


. 0.01089 


. 1 306 


0.01725 


0.02121 


0.02719 


0.03371 



' 



ENGINEER U>Ml- 
DATE. itrXC-?7« 



FIGURE 4.1.1. 1 -51 

EFFECT OF BODY FLAP 



U. 1.1. 1-56 



4* 



Rockwell Intematfonal 
Space Dhnaion 



L 



MACH NUMBER 



3.000 



Ll 
CO 

u 

Q 



.10 



.08 



.06 



.OH 



.03 



-.02 



-.OH 



I I I I 



DELBF COEG) 

-85 25 

| I I I I | i i l i | 



I I I 



1 r 



;^?fe 



i i i i 



I I '! 



_L_L 



till 



TTTrT 




I i i 



i I _L 



J_l L_L 



i I I T 



10 



15 



20 



as 30 

ALPHA CDEGD 



35 



HO 



H5 



50 



CONFIGURATION 


8ASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.055 FT. 


MOMENT REFERENCE ZO = U. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


OELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 






80DYFLAP NORMAL FORCE 


INCREMENT 






-11.700 


-0.00553 


-0.00856 


-0.01 110 


-0.01239 


-0.01528 


-0.01741 


-0.01980 


-5.000 


-0.00330 


-0.00H21 


-0 . 0053H 


-0 . 00635 


-0 . 00753 


-0 . 00665 


-0 . 00984 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00H56 


. 00567 


. 00652 


0.008C6 


0.01029 


0.01213 


0.01336 


10.000 


O.00S88 


0.01168 


0.01385 


0.01707 


0.02113 


. 02480 


. 02856 


16.300 


0.01607 


0.01942 


0.02361 


0.02995 


0.03498 


0.04070 


. 04632 


22 . 500 


0.02121 


0.02719 


0.03371 


0.04116 


. 04993 


. 05527 


0.061=2 



ENGINEER _ UJ*t- 
DATE 3Z"-kl-~)1 



FIGURE 4.1.1.1-52 
EFFECT GF BODY FLAP 



4.1.1.1-57 



SD72-SK-CCCC I M 



0$ 



Rockweit Interr -Mortal 

Space Division 



MACH NUMBER 
■'°i 1 I I I 



4.000 



DELBF CQEG) 

-25 25 



Q 




CONFIGURATION 


BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OT GRAVITY X0 « FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W » 78.056 FT. 


MOfCNT REFERENCE ZO = W_ 375.0 IN. 


M.A.C. CW ' 39.560 FT. 




BODY LENGTH LB ■ 1290.3 IN. 











ALPHA 


(DEG1 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0€LBF (C£G) 


A 


a 


C 





E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE 1NCRE 


"ENT 






-11.700 


0.0 


-0.00085 


-0.00160 


-0.00221 


-0.00286 


-O.C0456 


-0 . 00636 


-0.00847 


-5.000 


-0.00002 


-0.00038 


-0.00078 


-0.00127 


-0.00180 


-0.00268 


-0 . 00354 


-0 . 00492 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00007 


0.00040 


0. 00094 


0.00215 


0.00344 


0.00456 


. 00549 


. 00859 


10.000 


0.00020 


. 00083 


0.00201 


0.00465 


0.00735 


. 00976 


0.01221 


0.01779 


16.300 


0.00030 


0.00140 


0.00350 


0.00747 


0.01184 


0.01641 


0.02141 


0.02944 


22.500 


0.0 


. 00200 


0.00510 


. 00379 


0.01576 


. 02305 


0.03119 


0.04103 



ENG^ER__!'-' ,Vi '2- 

date Hiilzia 



FIGURE 4.1.1.1-53 

EFFECT C c B1C 



■LAF 



4-1.1 1- I 



*J> 



Rockwell International 

Space Division 



_L 



r 



MACH NUMBER 



4.000 



DELBF CDEG) 

-25 25 



li- 
en 

■z. 
u 

Q 



,10 



.08 



.OS 



.04 



.02 



-.02 



• OH 



I I I I I I I 



I ' ' ' 



I i~ 



F=e^--=^« g r-,- T 



i i i r 



iiii 



i i i i i i i i 



iiii 




i i i i 



i .i i i 



T~r 



10 



15 



20 



25 30 35 

ALPHA CDEGD 



HO 



45 



50 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2590.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BUI » 78.055 FT. 


MOMENT REFERENCE ZO = W_ 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


DELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 






BODYFLAP NORMAL FORCE 


INCREMENT 






-11.700 


-0.00456 


-0 . 00636 


-0.00847 


-0.01103 


-0.01457 


-0.01874 


-0.02361 


-5.000 


-0.00268 


-0 . 00364 


-0.00492 


-0 . 00639 


-0 . 00795 


-0 . 00969 


-0.01157 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00456 


. 00549 


0.00S59 


. 1 1 02 


0.01230 


0.01351 


0.01505 


10.000 


0.00976 


0.01221 


0.01779 


. 02346 


0.02563 


0.02940 


0.03241 


16.300 


0.01641 


0.02141 


. 02944 


0.03314 


. 04382 


. 04900 


0.05455 


22.500 


0.02305 


. 0.031 IS 


0.04103 


0.05127 


. 05978 


. 06638 


0.07472 



ENGINEER UiMT. 

OATE Z~AY-%T:~>t 



FIGURE 4.1.1.1-54, 

EFFECT. OF BODY FLAP 



4.1.1.1-59 



D 



/ ^ - 



-;-oceo im 



€> 



Rockwell International 

Space Division 



CQ 

Z 

u 
a 



MACHj NUMBER 
ilQ i I i | I I I I M 



.08 



.OS 



.OH 



.03 



-.03 



.04 



A A 



I I I 



;-*- 



5.000 
l I I I I l I 



DELBF CDEG) 

-25 85 



l I I I I I I 



I i I I 



TT 



i TT 



I I I I 







J__L 



I I ! 



I I I I 



I I I I 



I 1 I I 



I ! I 1 



-15 



-10 



5 
ALPHA 



10 

CDEGD 



20 



25 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO • FS 1076.7 IN. 


UING AREA SW » 2590.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW * 79.055 


FT. 


MOMENT REFERENCE ZO » WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BOOY LENGTH LB ' 1290.3 


IN. 







■ 


ALPHA 


1DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF ICEG) 


A 


B 


C 





E 


F 


G 


H 






BOOYFLAP NORMAL 


FORCE INC9E 


■-£NT 






-11.700 


0.0 


-0.00069 


-0.00 140 


-0.00214 


-0 . 002S6 


-0.00460 


-0.00632 


-0.00812 


-5.000 


0.0 


-0.00019 


-0.00051 


-0.00108 


-0.00170 


-0 . 00259 


-0.00354 


-0.00471 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00010 


0.00028 


• 0.00148 


0.00286 


. 00424 


. 00523 


. 00849 


10.000 


0.0 


-0.00033 


0.00039 


0.00321 


0.00521 


0.00896 


0.01 157 


0.01729 


16.300 


0.0 


-0.00056 


0.00070 


0.00513 


0.009S5 


• 0.01487 


. 02020 


. 02827 


22.500 


0.0 


-0.00039 


0.00140 


. 00650 


. 1 293 


. 02057 


0.02928 


. 03E96 



ENGII^£ER UM41. 
OATE UGlXCE"** 



FIGURE 4.1.1.1-55 

EFFECT OF BODY FLAP 



4.1.1.1-60 



'1* 



Rockwell International 

Space Division 



U- 

00 
Z 
CJ 
Q 



MACH NUMBER 

'°i I I I I I I I I ! 



5.000 



DELBF CDEG) 

-25 25 

I I l I | I I I I t 

I M I I'l I I I I I I 




,04 1 ' i I I I I I 1 1 I 1 
10 15 20 



30 35 

ALPHA CDEGD 



CONFIGURATION 




BASELINE ORSITER VEHICLE 


REFERENCE OI MENS IONS 




CENTER OF GRAVITY XO » PS 1076.7 IN. 


WING AREA SU = 2690.00 


SO. FT. 


OR YO = SL 0.0 IN. 


WING SPAN 8W » 78.056 


FT. 


MOMENT REFERENCE 20 - 14. 375.0 IN. 


M.A.C. CW • 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(CEG) 








15.000 


20 . 000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50 . 000 


DELEF (OEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BOOYF 


LAP NORMAL 


FORCE INCRE 


-ENT 






- 1 1 . 700 


-0 . 00460 


-0 . 00632 


-0.00812 


-0.01026 


-0.01392 


-0.01840 


-0.02369 


-0 . 02986 


-5.000 


-0.0025S 


-0.00354 


-0.00471 


-0.00605 


-0.00765 


-0.00948 


-0.01161 


-0.01407 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00424 


. 00523 


. 00849 


0.01063 


0.01173 


0.01289 


0.01469 


. 1 725 


10.000 


0.0C896 


0.01157 


0.01729 


0.02285 


0.02571 


0.02825 


0.03159 


. 03594 


16.300 


0.01487 


. 02020 


. 02827 


0.03700 


0.04253 


0.04760 


0.05329 


0.05947 


22.500 


. 02057 


. 02928 


0.03896 


0.G4889 


. 05720 


0.C6515 


. 07234 


0.05030 



ENGINEER UU^t 

date ZZi?Z£i-~>8 



FIGURE 4.1.1.1-56 

EFFECT OF BODY FLAP 



* 



k. 1.1.1-61 



SD7f.~3K~CCeC IM 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



8.000 



DELBF CDEG) 

-25 35 



.06 



m 
o 

Q 




m 



CONFIGURATION 



BASELINE 0R9ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO = WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN 8W = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

800Y LENGTH LB = 12S0.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


CELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE INCRE 


MENiT 






-11.700 


-0.00030 


-0 . 00082 


-0.00140 


-0.00201 


-0.00255 


-0.00382 


-0.00531 


-0.00718 


-5 . 000 


-0.00010 


-0 . 00020 


-0 . 00046 


-0.00093 


-0.00148 


-0 . 00225 


-0.00315 


-0.00431 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00007 


-0 . 00026 


0.00015 


. 00 1 1 


. 00234 


0.00388 


. 0C552 


0.00761 


10.000 


. C0C09 


-0 . 00056 


0.00012 


0.00238 


. 00534 


0.00855 


0. 01193 


0.01640 


16.300 


0.00003 


-0.00091 


0.0 


0.00379 


0.00841 


0.01368 


0.01946 


. 02690 


22.500 


-0.00018 


-0.00122 


-0.00020 


. 00360 


. O0S44 


. 1 739 


0.C2617 


0.0365! 



ENGINEER <M*V*- 

0ATE„__::3r:£ir-5ff 



FIGURE 4.1.1.1-57 
EFFECT OF BODY FLAP 



4.1.1.1-62 



* 



Rockwell International 

Space Division 



MACH NUMBER 



DELBF CDEG) 

-25 25 

I I l I | I I 



U 




30 35 

ALPHA CDEG 3 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE (DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO » a. 0.0 IN. 


WING SPAN BW ' 73.056 FT. 


MOMENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


OELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






800YF 


LAP NORMAL 


FORCE INCRE1 


hCNT 






-11.700 


-0.00382 


-0.00531 


-0.00718 


-0.00963 


-0.01357 


-0.01813 


-0.02336 


-0.02940 


-5.000 


-0 . 00225 


-0.00315 


-0.00431 


-0 . 00572 


-0 . 00744 


-0.00932 


-0.01141 


-0.01374 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00388 


0.00552 


0.00761 


0.00979 


0.01147 


0.01307 


0.01508 


0.01781 


10.000 


. 00855 


0.01193 


0.01640 


0.02143 


0.02506 


0.02823 


0.03149 


0.03564 


16.300 


0.01353 


0.01946 


. 02690 


0.03512 


0.04120 


0.04667 


0.05192 


. 05702 


22.5Q0 


. 1 739 


0.02517 


. 0365 1 


0.04703 


0.054S8 


0.05199 


. 0684 : 


0.074=5 



ENGINEER _ UJWZ. 

OATE Z.KzlT?78 



FIGURE 4.1.1.1-58 
EFFECT QF BODY FLAP 



4.1.1.1-63 



SD7L; -3H-C06C I M 



'1* 



Rockwell International 

Space Oh/ision 



MACH NUMBER 



10.000 



CD 

u 

a 



.10 



.09 



.06 



.04 



.02 



DELBF CDEG) 

-25 25 

I I I i 



-.02 



A A 



-.tfr M I I 1 I I I I I I I 



I I I I I I I i I I 



i I i i i i i i i i i I 'i~n~r 



i , A . *3*fl » \ %3»Se6^5-gSs 



*^¥± -- *>* — 



I I I I I I 



I I i I 




i I i I 



l i I I 



f---^r~^ 



l l I I 1 l l 



l I 1 1 l .l 



■15 



-10 



5 10 

ALPHA CDEG: 



15 



20 



25 



30 



CONFIGURATION 


baseline orbiter VEHICLE 


REFERENCE OlrCNSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO » 8L 0.0 IN. 


WING SPAN BW » 78.055 FT. 


MOfCNT REFERENCE 20 =■ W. 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BOOY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE INCRE 


MENT 






-11.700 


0.0 


-0.00067 


-0.00130 


-0.00186 


-0 . 00247 


-0.00360 


-0.00510 


-0.00697 


-5.000 


0.0 


-0.00015 


-0.00042 


-0 . 00087 


-0.00141 


-0.00218 


-0.00310 


-0.00421 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0 . 00022 


0.0 


0.00107 


. 00227 


0.00378 


. 00554 


0.00756 


10.000 


0.0 


-0.00062 


0.0 


0.00233 


. 0C527 


0.00851 


0.01200 


0.01587 


16.300 


0.0 


-0.00094 


0.0 


0.00371 


0.00334 


0.01374 


0.01956 


0.02652 


22.500 


0.0 


-0.00097 


0.0 


. 00345 


0.00916 


0.01751 


. 02660 


0.03717 



ENGINEER 
DATE 



=m* 



FIGURE 4.1.1.1-59 

EFFECT OF BODY FLAP 



U. 1.1. 1-64 



» 
V 



a 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



DELBF CDEG) 

-25 25 



U_ 
CO 

D 
o 




-.02 



.OH 



1 I I I 



r^ r ^- f ^£^f^p-7ri7r 



i i. i,i... 



i i i i 



i i i i 



i— LI. L 



till 



10 15 20 25 30 35 

ALPHA CDEG) 



i i i i 



-7 



! ! I 



I ! I I 



40 



45 



50 



55 



car i curat i on 




BASELINE 0R8ITER VEHICLE 


REFERENCE OIN-£NSrONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOCNT REFERENCE 20 = U_ 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


(DEG) 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45 . 000 


50.000 


DELBF (D£G) 


F 


G 


H 


I 


J 


K 


L 


M 






BODYF 


LAP NORMAL 


FORCE 1NCRE 


^ENT 






-11.700 


-0.00360 


-0.00510 


-0 . 00697 


-0 . 00949 


-0.01353 


-0.01B32 


-0.02335 


-0.02902 


-5.000 


-0.00213 


-0.00310 


-0.00421 


-0 . 00555 


-0 . 00739 


-0.00939 


-0.01 141 


-0.01358 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00378 


. 00554 


0.00756 


. 00938 


0.01120 


0.01303 


0.01505 


0.01771 


10.000 


0.00851 


0.01200 


0.01587 


0.01992 


0.02433 


0.02821 


0.03149 


0.03536 


16.300 


0.01374 


0.01966 


. 02652 


0.03368 


0.04050 


0.04578 


0.05197 


0.05651 


22.500 


0.01751 


. 02660 


0.03717 


0.04771 


0.05559 


0.06247 


0.06827 


. 07323 



ENGINEER 
DATE I 






FIGURE 4.1.1.1-60 
EFFECT OF BODY FLAP 



4.1.1.1-65 



SD72-3H OCCC 1M 



*> 



Rockwell International 

Space Division 



1_^ 



MACH NUMBER 



15.000 



OELBF CDEGD 

i I I i | I I I i | 



Q 



.10 



.08 



.06 



.04 



.02 



-.02 



-.OH 



I I I I I I I 



A A 



.1 I I I 



n — i i i i 



\ A .- Vs . VC <-..'"g.-aC* &>*, 



I'll 



I I ' 



*^=t~Z 



MIT 



I I I i I I I 






5^ 



1 l l l 



1. 1 1 l 



1 1 l l 



1 1 1 1 



■■^ 



1 1 ' 1 




J_L 



-15 



-10 



5 10 

ALPHA CDEGD 



15 



■«. 20 



25 



30 



CONFIGURATION 



BASELINE ORSITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO = 8L 0.0 IN. 

MOMENT REFERENCE ZO » WL 375.0 IN. 



REFERENCE (MANSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW =■ 39.560 FT. 
BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


CSLBF (C€G) 


A 


B 


C 





E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE 1NCREJ 


"ENT 






-11.700 


0.0 


-0.00067 


-0.00130 


-0.00186 


-0.00247 


-0.00360 


-0.00510 


-0 . 00697 


-5.000 


0.0 


-0.00015 


-0.00042 


-0.00087 


-0.00141 


-0.00218 


-0.00310 


-0.00421 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00022 


0.0 


0.00107 


0.00227 


0.00378 


0.00554 


. 00755 


10.000 


0.0 


-0.00062 


0.0 


0.00233 


0.00527 


0.00851 


0.01200 


0.01587 


16.300 


0.0 


-0.0009+ 


0.0 


0.00371 


. 00834 


0.01374 


0.01966 


0.02552 


22.500 


0.0 


-0.00097 


, °-° 


0.00345 


0.00916 


0.01751 


. 02660 


0.03717 



ENGINEER UIM^. 
DATE Z_±-.1L-~>8 



FIGURE 4.1.1.1-61 

FFFFCT OF BODY FLAP 



4.1.1.1-66 



SD72-SH-CCCC 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



15.000 



DELBF CDEG) 

-25 25 



f-J 




30 35 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS ' 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW • 78.056 FT. 


MOfENT REFERENCE ZO « W_ 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








15.000 


20 . 000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50 . 000 


DELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOYF 


LAP NORMAL 


FORCE INCRE 


"OJT 






-11.700 


-0.00360 


-0.00510 


-0.00697 


-0.00949 


-0.01358 


-0.01832 


-0 . 02336 


-0 . 02902 


-5.000 


-0.00218 


-0.00310 


-0. 00421 


-0.00556 


-0.00739 


-0.00939 


-0.01141 


-0.01358 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00378 


. 00554 


0.00756 


0.00938 


0.01120 


0.01303 


0.01505 


0.01771 


10.000 


0.00851 


0.01200 


0.01587 


0.01992 


0.02433 


0.02821 


0.03149 


. 03536 


16.300 


0.01374 


0.01965 


0.02652 


0.03368 


. 04050 


. 04673 


0.05197 


0.05651 


22.500. 


0.01751 


0.02560 


0.03717 


0.04771 


. 05559 


0.05247 


0.06827 


. 07323 



ENGINEER WMT^ 
DATE "I^AJ-na 



FIGURE 4.1.1.1-62 
EFFECT OF BODY FLAP 



4.1.1.1-67 



€> 



Rockwell International 

Space Division 



MACH NUMBER 



20.000 



u. 

CO 

o 



.10 



.08 



.OS 



.OH 



.02 



DELBF CDEG] 

25 25 

till 



.02 



I I I I I I I I I I I I I I I I I I 



A A 



.04' I ' ' 
-15 



I I I I . 



I I I I 



J L I 



-10 




— ~ -G-ST — ~ TZ- 



10 

CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR . YO - BL 0.0 IN. 

MOtENT REFERENCE ZO =■ UL 375.0 IN. 



REFERENCE D^NSIONS 
WIN3 AREA SW = 2690.00 SQ.FT. 
WING SPAN BUI = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB * 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOYF 


LAP NORMAL 


FORCE INCRE 


r-ENT 






-11.700 


0.0 


-0.00067 


-0.00130 


-0.00186 


-0.00247 


-0.00360 


-0.00510 


-0.00697 


-5.000 


0.0 


-0.00015 


-0.00042 


-0.00087 


-0.00141 


-0.00218 


-0.00310 


-0.0042! 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00022 


0.0 


0.00107 


0.00227 


0.00378 


0.00554 


. 00756 


10.000 


0.0 


-0.00062 


0.0 


0.00233 


0.00527 


0.00851 


0.01200 


0.01587 


16.300 


0.0 


-0.00094 


0.0 


0.00371 


. 00834 


0.01374 


0.01966 


0.02652 


22.500 


0.0 


-0.00097 


0.0 


0.00345 


0.00916 


0.01751 


. 02550 


0.03717 1 



ENGINEER OJAA'L. 
DATE I"f>Z1j-7g 



FIGURE 4.1.1.1-63 
EFFECT GF BODY FLAP 



4.1.1.1-68 



SD72-3H~CCC : .G 1 M 



€> 



Rockwell International 
Spac* Otvision 

I 



MACH NUMBER = 20. 000 

10 ' i i i i I I ] i i I i l l I I I 



DELEF (DEG) 
-25 25 



Ll 



a 




30 35 

ALPHA CDEG) 



CONFIGURATION 


BASEL INE CRBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW ' 39.560 FT. 




BODY LENGTH LB * 1290.3 IN. 











ALPHA 


<DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45. GCO 


50.000 


DELBF (OEG) 


F 


G 


H 


I 


J 


K 


• L 


M 






BOOYF 


LAP NORMAL 


FORCE INCRE 


*ENT 






-11.700 


-0.00360 


-0.00510 


-0.00697 


-0. 00949 


-0.01359 


-0.0ie32 


-0 . 02336 


-0 . 029C2 


-5.000 


-0.00218 


-0.00310 


-0.00421 


-0.00556 


-0 . 00739 


-0 . 00939 


-0.01141 


-0.01358 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00378 


0.00554 


0.00756 


0.00938 


0.01120 


0.01303 


0.01505 


0.01771 


10.000 


0.00851 


0.01200 


0.01587 


0.01992 


0.02433 


0.02821 


0.03149 


0.03536 


16.300 


0.01374 


0.01S66 


0.02652 


. 03368 


0.04050 


. 04678 


0.05197 


. C555 1 


22.500 


0.01751 


. 02560 


0.03717 


0.04771 


. 05559 


0.05247 


. 06327 


0.07323 



ENGif^ER _U)M7~ 

date I_5r-£I-"?8 



FIGURE 4.1.1.1-64 

EFFECT CF BODY FLAP 



4.1.1.1-69 



a 



Rockwell International 
Spaca Division 



VBAR 

■ 08 i' r i i i I i i i i 



0. 005 through 0.080 



DELBF CDEG) 

25 25 

I I I I | I I I I | 




-.02 



30 35 40 

ALPHA CDEGD 



CONFIGURATION 




BASELINE ORBITER CHICLE 


REFERENCE OltCNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MO£NT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 





. ALPHA (OEG) 


20.000 


25.000 


30:000 


35.000 


40.000 


45.000 


50.000 


OELBF <C€G) 


A 


B 


C 





E 


F 


G 






BCOY FLAP NORMAL FORCE 


INCREf-EN 






-11.700 


-0.00510 


-0.00697 


-0.00949 


-0.01358 


-0.01832 


-0.02336 


-0.02902 


-5.000 


-0.00310 


-0.00421 


-0.00556 


-0.00739 


-0.00939 


-0.01I4I 


-0.01358 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00554 


0.00756 


0.0033S 


0.01120 


0.01303 


0.01505 


0.01771 


10.000 


0.01200 


0.01587 


0.01992 


0.02433 


0.02321 


0.03149 


0.03536 


16.300 


0.01966 


0.02652 


0.03368 


0.04050 


0.04678 


0.05197 


0.05551 


22.500 


0.02660 


0.03717 


0.04771 


0.05559 


0.06247 


0.06827 


0.07323 



ENGINEER __NASA 
OATE I„~~ 



FIGURE 4.1.1.1-65 

EFFECT OF BODY FLAP 



4.1.1.1-70 



SD72-si-:-ccec iivi 



€* 



Rockwell International 

Space Division 



ALTITUDE CFT.D = 300,000 to 600,000 

.08 1 — i — i — i — i — i — i — i — i — i — i — i — i — i — i — i — i — \ — i — i — \ — | — | — i — r 



DELBF CDEG: 

-25 25 



u. 

CO 

y 




-.04 



30 35 HO 

ALPHA CDEG) 



COM 7 1 (JURATION 


BASELINE CRSITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER CF GRAVITY XO = F5 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MCttNT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 





ALPHA CDEG) 




20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELBF <DEG) 


A 


B 


C 





E 


F 


G 






BODY FLAP NORMAL FORCE 


INCREfEN 






-11.700 


-0.00510 


-0 . 00697 


-0.00949 


-0.01358 


-0.01832 


-0 . 02336 


-0.02902 


-5.000 


-0.00310 


-0.00421 


-0.00556 


-0.00739 


-0 . 00939 


-0.01141 


-0.01358 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00554 


0.00756 


0.00938 


0.01120 


0.01303 


0.01505 


0.01771 


10.000 


0.01200 


0.01567 


0.01992 


0.02433 


0.02821 


0.031H9 


0.03536 


16.300 


0.01966 


0.02652 


0.03368 


0.04050 


. 04678 


0.05197 


0.05651 


22.500 


0.02660 


0.03717 


0.04771 


0.05559 


0.06247 


0.06827 


0.07323 



ENGINEER NASA 
DATE ~ 



FIGURE 4.1.1.1-66 

EFFECT GF BODY FLAP 



..1.1.1-71 



a 



Rockwell International 

Space Division 



MACH NUMBER = 0.250 

•02[' | j ! I I I I I I I I I I I I IT I i I I I i i I I i i 



DELSB CDEG) 

50 100 



CO 

cn 
a 




10 

ALPHA 



conf I guration 



BASELINE 0R3ITER VEHICLE - 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO » WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 26S0.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW =» 39.560 FT. 
BODY LENGTH LB - 1390.3 IN. 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELS8 (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






SPEE 


06RAKE NORMAL FORCE IN 


:r. 






0.0 


0.00787 


0.00936 


0.00970 


0.0081S 


0.00684 


. 00652 


0.00535 


. 00532 


15.000 


0.00515 


0.00450 


0.00400 


. 00359 


0.00324 


0.002S6 


0.00273 


0.00303 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00533 


-0.00515 


-0 . 00500 


-0.004S6 


-0 . 00504 


-0 . 00463 


-0.00427 


-0 . 00508 


45.000 


-0.01039 


-0.01015 


-0.01000 


-0.01 009 


-0.01047 


-0.01026 


-0.01010 


-0.01032 


55.000 


-0.01553 


-0.01522 


-0.01490 


-0.01467 


-0.01484 


-0.01521 


-0.01567 


-0.01685 


70.000 


-0.02101 


-0.02=63 


-0.02350 


-0.02331 


-0.02357 


-0.02516 


-0.02714 


-0.028S2 


87.200 


-0.02619 


-0 . 02e25 


-0.03020 


-0.03225 


. -0,03442 


-0.03640 


-0 . 03S54 


-0-04129 



ENGINEER J- <lb 
DATE_A3r3»B- 



FIGURE 4.1.1.1-67 

EFFECT OF SPEEDBRAKE 



4.1.1.1-72 



SL" 7 



3H 



coec 1M 



* 



Rockwell International 
Space Division 



MACH NUMBER 



0.400 



DELSB CDEGD 

50 ICO 

| I I i I 



CO 
CO 

u 




-.06 



10 

ALPHA 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW * 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE 20 - W_ 375.0 IN. 


M.A.C. CW =» 39.560 


FT. 




BODY LENGTH L9 = 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5. COO 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELS8 (DEC) 


A 


3 


C 


D 


E 


F 


G 


H 






SPEE 


D3RAKE NORMAL FORCE IN 


:r. 






0.0 


. 00787 


0.00936 


. 00970 


0.00818 


0.00684 


. 00652 


. 00635 


0.00532 


15.000 


0.00515 


0.00450 


0.00400 


0.00359 


0.00324 


0.00296 


0.0C273 


0.00303 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00533 


-0.00515 


-0.00500 


-0 . 00496 


-0 . 00504 


-0 . 00453 


-0 . 00427 


-0 . 00508 


45.000 


-0.01039 


-0.01015 


-0.01000 


-0.01009 


-0.01047 


-0.01025 


-0.01010 


-0.01032 


55.000 


-0.01553 


-0.01522 


-0.01490 


-0.01467 


-0.01484 


-0.01521 


-0.01567 


-0.01635 


70 . 000 


-0.02101 


-0.02263 


-0.02350 


-0.02331 


-0 . 02357 


-0.C2516 


-0.02714 


-0 . 02392 


87 . 200 


-0.02519 


-0.02825 


-0.03020 


-0 . 03225 


-0 . 03442 


-0.03640 


-0.C3S54 


-0.04129 



engineerJE*^ _ 

DATE _J^r_5jil$- 



FIGURE 4.1.1.1-68 

EFFECT OF SPEEDBRAKE 



4.1.1.1-73 



'» 



Rockwell International 

Space Division 



MACH NUMBER 



0.600 



0ELS8 CDEG) 

50 100 

I I l I I I i I I 



.02 



s: 



00 

in 

8 



.02 



-.04 



-.OS 



-.08 



-10 



I 1. I 



I I I i 



I I I I 



Till 



I...I I ! 



ii r 




i i i i 



n ft 



i i 



T ,TT 



i i I I 



to 
ALPHA 



15 

CDEG) 



20 



25 



30 



35 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 107B.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W = 78.056 FT. 


MOMENT REFERENCE ZP - WL 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELSS (DEG) 


A 


B 


C 





E 


F 


G 


H 






SPEE 


D8RAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.00979 


. 00S92 


0.01000 


. 00932 


. 00845 


0.00766 


0.00704 


0.00659 


15.000 


0.00661 


. 00580 


0.00500 


0.00416 


0.00394 


0.00418 


0.00443 


. 00467 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00461 


-0.00412 


-0 . 00639 


-0.00500 


-0.00455 


-0.00236 


-0.00241 


-0.00082 


45-000 


-0 . 00975 


-0.01002 


-0.012S9 


-0.01035 


-0 . 00958 


-0 . 0C637 


-0.00489 


-O.0C442 


55.000 


-0.01653 


-0.01753 


-0.01882 


-0.01604 


-0.01478 


-0.01222 


-0 . 00997 


-0 . 00804 


70 . 000 


-0 . 02405 


-0 . 02558 


-0.02746 


-0 . 025^2 


-0.02432 


-0.02131 


-0.01888 


-0.01705 


87.200 


-0.03194 


-0.03421 


-0.03711 


-0.03742 


-0.03579 


-0 . 03854 


-0.C40S5 


-0.04360 



ENG!NEERJ>6«E> 

DATE„b2rSrrSI 



FIGURE 4.1.1.1-69 

EFFECT OF SPEEDBRAKE 



4.1.1.1-74 



SD72-SH-CC6C IM 



* 



Rockwell International 

Space Division 



MACH NUMBER 



OELSB CDEGD 

50 100 



CO 
'Si 

~Z. 

Q 




-.06 



CONFIGURATION 



BASELINE CR9ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MCfENT REFERENCE ZO » WL 375.0 IN. 



REFERENCE 01 PENSIONS 
WING AREA SW = 5690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25. CC0 


DFLSB ( DEG ) 


A 


8 


C 


D 


E 


F 


G 


H 






SPEE 


C8RAKE NORM 


AL FCRCE IN 


:r. 






0.0 


0.01100 


0.0105H 


0.01000 


. 00946 


0.01023 


0.00984 


. 00345 


. 00SC5 


15.000 


. 00570 


0.00532 


0.00500 


0.00424 


. 00507 


0.00479 


0.00448 


0.00414 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00700 


-0.00723 


-0.00727 


-0 . 00548 


-0.00408 


-0 . 00368 


-0.00353 


-0 . 00362 


45.000 


-0.01H33 


-0.01507 


-0.01563 


-0.01164 


-0.00913 


-0.00838 


-0.00800 


-0.00739 


55.000 


-0.02246 


-0.02341 


-0.02450 


-0.01843 


-0.01555 


-0.01475 


-0.0143B 


-0.01442 


70 . 000 


-0.04047 


-0.03802 


-0 . 03599 


-0.03205 


-0.02614 


-0.02621 


-0.02699 


-0.C2S42 


87.200 


-0 . 057£2 


-0 . C5356 


-0 . 05038 


-0.04640 


-0 . 04 1 30 


-0.04341 


-0 . C4640 


-0 . 050 1 3 



ENGINEER i^j-L. 
OATE_JJi.r-ir— V_ 



FIGURE 4.1.1.1-70 

FFFFCT OF SPEE03RAKE 



U. 1.1. 1-75 



SD72-SH-CCbG 1 iv'l 



* 



Rockwell International 

Space Division 



MACH NUMBER 



0.900 



DELSB CDEG) 

50 100 

T"T i 



CQ 
CO 

-z. 
u 

Q 



-.06 



-.08 




CONFIGURATION 



BASELIMZ 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1075.7 IN. 

OR YO = BL 0.0 IN. 

MOMENT REFERENCE ZP - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB - 1890.3 IN. 











ALPHA 


(CEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CCLSB (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


D6RAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.01058 


0.01037 


0.01000 


0.01013 


0.01174 


0.00992 


0.00813 


0.00657 


15.000 


0.00593 


0.00576 


. 00550 


0.00518 


0.00567 


0.00497 


. 00425 


0.00356 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.01035 


-0 . 00972 


-0.00885 


-0.00707 


-0.00505 


-0.00343 


-0 . 00202 


-O.00C85 


45.000 


-0.02298 


-0.02070 


-0.01829 


-0.01482 


-0.01093 


-0.00809 


-0 . 00556 


-C. 00369 


55.000 


-0.03677 


-0 . 03227 


-0.02800 


-0.02284 


-0.01767 


-0.01430 


-0.01152 


-0 . 00936 


70.000 


-0.04689 


-0.04440 


-0.04050 


-0.03501 


-0.03001 


-0.02479 


-0.02003 


-0.01578 


87.200 


-0.05511 


-0 . 05464 


-0 . 05500 


-0.05107 


-0.04653 


-0 . 03=88 


-0.03409 


-0 . 02922 



ENGINEER b&C> 
DATE„JL<£E}£-Jf£ 



FIGURE 4.1.1.1-71 
■ . EFFECT OF SPEEDBRAKF 



4.1.1.1-76 



* 



Rockwell International 

Space Division 



MACH NUMBER 



0.350 



OELSB CDEG) 

50 1 00 

Mil 



m 

in 

z 

a 




CONFIGURATION 


BASELINE ORB ITER VEHICLE 


REFERE>CE DIMENSIONS 


CENTER CF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2630.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 79.056 FT. 


MCttNT REFERENCE 20 = W_ 375.0 IN. 


M.A.C. CW = 29.560 FT. 




BODY LENGTH LB = 1230.3 IN. 











ALPHA 


CDEG1 








-10.000 


-5.000 


0.0 


5 . 000 


10.000 


15.000 


20. COO 


25.000 


OELSB (OcG) 


A 


S 


C 


D 


E 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.01098 


0.01048 


0.01000 


0.00954 


0.01153 


0.00951 


. 00756 


0.00577 


15.000 


0.00707 


0.00671 


0.00630 


0.00474 


. 00544 


0.00414 


. 00290 


0.00187 


£5.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.01028 


-0 . 00S65 


-0 . 00892 


-0 . 00446 


-0.00544 


-0.00381 


-0 . 00247 


-0.00145 


45.000 


-0.02105 


-0.01956 


-0.01814 


-0.01064 


-0.01 178 


-0 . 00874 


-0.00525 


-0 . 004^0 


55.000 


-0.03211 


-0 . 02957 


-0 . 02750 


-0 . ! 925 


-0.01913 


-0.01479 


-0.01128 


-0.00865 


70.000 


-0 . 04662 


-0.04305 


-0.04000 


-0.03383 


-0.03209 


-0 . 02475 


-0.01346 


-0.01340 


87 . 200 


-0 . 06630 


-0.06094 


-0 . 05650 


-0 . 05-67 


-0 . 04965 


-0 . 03795 


-0 . 02763 


-0.01904 



ENGINEER l&Z> 
OATE.jOfZr^S 



FIGURE 4. 1. 1. 1- 72 

EFFECT OF SPE EDBRAKE 



4.1.1.1-77 



SD72 



S H - C C e C 



M 



€* 



Rockwell International 

Space Division 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN 

OR YO - a. 0.0 IN 

MOMENT REFERENCE ZO » 14. 375.0 IN 



ON 




REFERENCE DIMENSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW - 78.056 


FT. 


M.A.C. CW » 39.560 


FT. 


BODY LENGTH LQ = 1290.3 


!N. 



DELS8 (DEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA I DEO) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



SPEEDBRAKE NORMAL FORCE I NCR 



0.01100 
. 00705 
0.0 
-0.00985 
-0.01973 
-0.02966 
-0.04509 
-0.06601 



0.01047 
0.00665 
0.0 
-0.00919 
-0.01850 
-0.02789 
-0.04171 
-0.06004 



0.01000 
0.00623 
0.0 
-0.00852 
-0.01736 
-0 . 02637 
-0.03882 
-0.05503 



. 00956 
. 00463 
0.0 
-0.00434 
-0.01032 
-0.01870 
-0.03309 
-0.0517! 



0.01148 
0.00533 
0.0 
-0.00538 
-0.01160 
-0.01682 
-0.03135 
-0 . 04874 



0.00954 
0.00395 
0.0 

-0.00376 
-0 . 00852 
-0.01428 
-0.02384 
-0.03611 



0.00767 
0.00278 
0.0 

-0.00237 
-0.00598 
-0.01057 
-0.01674 
-0 . 02425 



. 00596 
0.00187 
0.0 
-0.00141 
-0 . 00397 
-0.00767 
-0.01111 
-0.0142S 



ENGINEER pG>X> 
DATE__l9_-5--r5' 



FIGURE 4.1.1.1-73 

EFFECT OF SPEEDBRAKE 



4.1.1.1-78 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.050 



DELSB CDE6) 

50 1 00 

I I I I I I I I ! I 



CD 

in 
o 



-.05 





SZZT- 




111 ! 



"1 I I i ' I I I i 



Btf 




j-_j_j_j- 



.t^- 




_L. 



I I I 



: =^==^ 




I I 1 




;ti^*7* 



i i i 



■ t i i 



10 

ALPHA 



15 
CDEGD 



20 



25 



30 



35 



CONFIGURATION 


BASELINE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER CF GRAVITY XO = FS 1076.7 IN. 


HlNG AREA SW ■ 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE ZO = W. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(CEG) 








-10.000 


-5 . 000 


0.0 


5.000 


1 . 000 


15.000 


20.000 


25.000 


OELSB (DEG) 


A 


8 


C 


D 


c 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.01069 


0.01026 


0.01000 


. 00980 


0.01156 


0.01008 


0.00862 


0.00721 


15.000 


0.0C551 


0.00526 


0.00507 


. 00458 


. 00493 


. 00388 


0.00297 


0.00211 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00759 


-0 . 00698 


-0 . 00653 


-0.00525 


-0 . 00472 


-0.00336 


-0.00214 


-0.00119 


45.000 


-0.01604 


-0.01479 


-0 . 1 385 


-0.01157 


-0 . 00993 


-0.00700 


-0 . 00434 


-0.00204 


55.000 


-0 . 02467 


-0 . 02345 


-0.02179 


-0.0I9C2 


-0.01622 


-0.01156 


-0 . 00730 


-0.00354 


70.000 


-0.04022 


-0.03694 


-0.03420 


-0.03145 


-0.02792 


-0.C1976 


-0.01159 


-0 . 00452 


87.200 


-0,06097 


-0 . 05529 


-0 . 05077 


-0 . 0480 ! 


- 0.04440 


-0.03070 


-0.01765 


-0 . 00605 



ENGINEER fc^Z> 

date LQr_2?ri£> 



FIGURE 4. 1.1.1- 1U 

EFFECT GF SPEEDBRAKE 



4.1.1.1-79 



SD7 



SH 



ooeo im 



* 



Rockwell International 

Space Division 



MACH NUMBER 



CD 

z 
u 
a 




DELSB CDEGD 

50 100 

i I I I 



-.02 



-.OH 



.06 



.08 



I I 1 



I I I I 



1111 



111! 



_L 



J i 



LI 1 1 . 



I I I I 



riH ^H 



-10 



10. 

ALPHA 



15 

CDEG3 



20 



30 



55 



CONFIGURATION 




BASELISE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCHENT REFERENCE ZP =» ML 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BOOY LENGTH L8 » 1290.3. 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEG) 


A 


B 


C 





E 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.01062 


0.01019 


0.01000 


0.00S88 


0.01153 


0.0102S 


. 00900 


. 00778 


15.000 


0.00511 


0.00485 


. 00468 


. 00457 


. 00473 


0.00392 


0.00314 


0.00240 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00659 


-0 . 00603 


-0.00555 


-0.00547 


-0.00448 


-0.00318 


-0.0019S 


-0.00085 


45.000 


-0.01386 


-0.01290 


-0.01220 


-0.01175 


-0.00929 


-0.00634 


-0.00355 


-0.00098 


55.000 


-0.02227 


-0 . 02059 


-0.01950 


-0.01867 


-0.01515 


-0.01029 


-0.00571 


-0.00149 


70.000 


-0.C3766 


-0.03437 


-0.03180 


-0.03021 


-0.02613 


-0.01780 


-0.01000 


-0 . 00295 


87.200 


-0.05881 


-0 . 05279 


-0 . 04800 


-0 . 04526 


-0.04150 


-0 . 02834 


-0.01608 


-0 . 00495 



ENGIf^ER TX*D 
DATE LGLzjfcOib 



FIGURE 4.1.1.1-75 

EFFECT. OF SPEEDBRAKE 



4.1.1.1-30 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.200 



OELSB CDEG) 

50 100 



CD 
CO 

u 

Q 




-.08 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2590.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOMENT REFERENCE 20-14. 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB « 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (CEG) 


A 


B 


c 


D 


E 


F 


G 


H 






SPEE 


D6RAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.01295 


0.01145 


0.01000 


0.00955 


0.01110 


. 00985 


0.00874 


0.00781 


15.000 


0.00749 


. 0064 1 


. 00550 


0.00459 


0.C0485 


0.00418 


0.00364 


0.00322 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.01099 


-0 . 00876 


-0 . 00667 


-0.00495 


-0.00485 


-0.00316 


-0. 00 128 


. 00072 


45.000 . 


-0 . 02056 


-0.01687 


-0.01333 


-0.01043 


-0.01015 


-0.00652 


-0.00291 


. 00C63 


55.000 


-0.02880 


-0.02436 


-0.02000 


-0.01649 


-0.01573 


-0.01042 


-0 . 00557 


-0. 00 125 


70.000 


-0 . 04250 


-0 . 03656 


-0.03100 


-0.02708 


-0.02453 


-0.01855 


-0.01344 


-0 . 00933 


87.200 


-0.05677 


-0.04951 


-0 . 04300 


-0.03942 


-0.03656 


-0.02888 


-0.02241 


-0.01725 



ENGINEER £*^b 
DATE Sr2fr!!2S> 



FIGURE 4.1.1.1-76 
. EFFECT OF SPEEDBRAKE 



4.1.1.1-81 



SD7 



COCO IM 



^W Rockwell International 

Space Division 



1 



MACH NUMBER 



1.300 



DELSB CDEG) 

50 100 

T"l I I 



:r^sgr=r=r^r 



m 
en 

8 



i i r 




CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BCOY LENGTH LB » 1590.3 IN. 



CELS8 (DEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



-10.000 
A 



-5.000 

s . 



0.0 

c 



ALPHA (DEG) 



5.000 




10.000 
E 



15.000 

F 



0.01183 
0.00608 
0.0 
-0.00958 
-0.01813 
-0.025B7 
-0 . 03750 
-0.05112 



0.01099 
0.00531 
0.0 
-0.00768 
-0.01511 
-0.02226 
-0.03291 
-0.04540 



SPEEDSRAKE NORMAL FORCE 1NCR. 



20.000 
G 



25.000 
H 



0.01000 
0.00475 
0.0 
-0.00592 
-0.01223 
-0.01875 
-0 . 02849 
-0.03973 



0.00901 

. 00464 

0.0 
-0.00449 
-0.00936 
-0.01489 
-0.02457 
-0.03654 



0.01016 
0.00468 
0.0 
-0 . 00429 
-0.00895 
-0.01405 
-0.02193 
-0.03315 



0.00991 
0.00431 
0.0 
-0.00337 
-0.00676 
-0.01038 
-0.01750 
-0 . 02ES4 



0.00978 
0.00401 
0.0 
-0.00235 
-0.00455 
-0.00638 
-0.01389 
-0.02145 



0.00976 
0.00379 
0.0 
-0.00125 
-0.00230 
-0.00389 
-0.01087 
-0.01713 



ENGINEER £*SJ> 
OATE.jOjl3»"f1g 



FIGURE 4.1.1.1-77 

EFFECT OF SPEEDBRAKE 



4.1.1.1-82 



SD'72-SH-00e0 JM 



€> 



Rockwell International 

Space Division 



MACH NUMBER 



1.500 



OELSB CDEG) 

50 100 

I I ! > I I l I 



CD 
on 




10 

ALPHA 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO ' FS 107S.7 IN. 

OR YO » BL 0.0 IN. 

MOENT REFERENCE ZO - W_ 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW « 39.560 FT. 

BOOY LENGTH L3 = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (OEG) 


A 


S 


c 


O 


E 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.00979 


. 00990 


0.00960 


. 00807 


0.00852 


0.00959 


0.01051 


0.01145 


15.000 


. 00424 


0.00392 


. 00379 


0.00440 


0.00417 


0.00412 


0.00412 


0.00414 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00745 


-0.00616 


-0.00476 


-0 . 00379 


-0.00327 


-0.00354 


-0.00345 


-0.00322 


45 . 000 


-0.01456 


-0.01259 


-0.01030 


-0.00782 


-0.00685 


-0.00682 


-0.0C608 


-0.00507 


55.000 


-0.02132 


-0.01867 


-0.01635 


-0.01251 


-0.01136 


-0 . 00997 


-0.00818 


-0 . 00674 


70 . 000 


-0.02996 


-0 . 02694 


-0.02405 


-0.02112 


-0.01853 


-0.01598 


-0.01416 


-0.01 3C4 


67.200 


-0.04261 


-q. 03852 


-0 . 03462 


-0.03180 


-0.02813 


-0.02379 


-0.02014 


-0.01 7E9 



ENGINEER $&& 
OATE_J_o_-_5_OS 



FIGURE 4.1 
EFFECT 



.1.1-78 

OF SPEED6RAKE 



4.1.1.1-83 



SD72-SH-0CCC IM 



€* 



Rockwell International 
Space Division 



MACH NUMBER = 2.000 

- 02 ' - ' I i I I I I I l I I I I I I l l l I 



DELSB CDEGD 

50 100 



CD 

en 
a 



-.04 



.05 



-.08 



I I I I I I 1 I I I I I I 



tt r 




II I I II I II I I 



iii: — i i n 



I I I I I I i I I I 



I I I I I ! I 



1 TTT 



-10 



10 15 20 

ALPHA CDEG3 



25 



30 



35 



HO 



CONFIGURATION 




BASELINE ORB1TER VEHICLE 


REFERENCE DINtNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YD - BL 0.0 IN. 


WING SPAN SW » 78.056 


FT. 


MOf-ENT REFERENCE 20 « WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB * 1290.3 


IN. 





ALPHA (DEG) 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


30.000 


DELSB (DEG) 


A 


B 


C 





E 


F 


G 


H 


I 








SPEEDBRAKE 


NORMAL FOR 


CE I NCR. 








0.0 


0.00698 


0.00675 


0.00650 


0.00623 


0.00657 


0.00599 


0.00539 


0.00483 


0.00433 


15.000 


0.00354 


0.00324 


0.00295 


. 00268 


0.00240 


. 00234 


0.00208 


0.00179 


0.00148 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00462 


-0.00399 


-0.00342 


-0.00292 


-0.00206 


-0.00220 


-0.00187 


-0.00139 


-0.00078 


45.000 


-0.01024 


-0.00876 


-0 . 00738 


-0.00611 


-0.00475 


-0.00476 


-0.00404 


-0.00325 


-0 . 00239 


55.000 


-0.01594 


-0.01370 


-0.01161 


-0 . 00969 


-0.00867 


-0.00755 


-0.00657 


-0 . 00570 


-0.00494 


70.000 


-0.02334 


-0.02047 


-0.01800 


-0.01694 


-0.01518 


-0.01207 


-0.01130 


-0.01075 


-0.01041 


87.200 


-0 . 03496 


-0.03068 


-0 . 02700 


-0.02397 


-0.02156 


-0.02025 


-0.01938 


-0.01903 


-0.01S20 



ENGINEER j>^cp> 
DATE_joI-23o££ 



FIGURE 4.1.1.1-79 

EFFECT OF SPEEDBRAKE 



U. 1.1. 1-34 



*> 



Rockwell International 

Space Division 



R 



m 
en 

Q 



MACH NUMBER 



3.000 



.02 



DELSB CDES) 

50 100 

I I i 



.0 



sr—fcrfc 



1 __Scl. ' ^- -N^-+ ISv.j. - ii~g — 



.02 



.04 



.06 




.08 



I I I I 



Mil 



I I I I 



I i I I 



I I I i 



I .L , I I 



I I i i 



■TSi^-t^- 



i i i i 



I I I 1 



i i i i 



i i i 






il IT 



1 I I 



I I I l 



■L 1-1. J. 




I , I.I 



J J... I !. 



•10 



10 

ALPHA 



15 

CDEGD 



20 



25 



30 



35 



CONF 1GURATICN 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W - 78.056 FT. 


MOMENT REFERENCE 20 - U_ 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BCOY LENGTH LB = 12SQ.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


D8RAKE NORM 


AL FORCE IN 


;r. 






0.0 


0.00928 


. 00837 


0.00755 


0.00685 


0.00639 


0.00508 


. 00538 


0. 004 12 


15.000 


0.00371 


0.00335 


0.00302 


0.0027V 


0.00256 


0.002H3 


0.00215 


0.00155 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00390 


-0 . 00353 


-0.00318 


-0 . 00286 


-0.00269 


-0 . 00267 


-0.00240 


-0.00181 


45.000 


-0.00692 


-0.00617 


-0 . 00559 


-0.00518 


-0. 00474 


-0.0C427 


-0 . 00365 


-0 . 00294 


55.000 


-0.00S5O 


-0 . 00838 


-0.00760 


-0.00717 


-0 . 00638 


-0 . 00520 


-0.00430 


-0.00355 


70 . 000 


-0.01379 


-0.01272 


-0.01300 


-0.01175 


-0.01036 


-0 . 00975 


-0.00741 


-0.0G544 


87.200 


-0.02065 


-0.01957 


-0.01897 


-0.01882 


-0.01766 


-0.01725 


-0.01275 


-O.0CSS8 



ENGINEER ~>£:D 

DATE_Jo.r_5r-.~i5 



FIGURE 4.1.1.1-30 

EFFECT GFSPEEDBRAKE 



k. 1.1.1-35 



S-D72 -SH-CCcO IM 



«L* 



Rockwell International 

Space Division 



-^ 



MACH NUMBER 



3.000 



DELSB CDEG) 

50 100 



.02 



' ^^V-V^^JIV^^hC--------- ^a.— ---- -L-a.. L . 



CD 

tn 

■z. 

a 



.02 



.04 



-OS 



-.08 



15 



t i i i I i ! i i i i i i i I i i i i i i r 



i i i 



i i i i 
i i i i 



i i i i i 
i i i i 



iiii 



i i 



i i 



i i i i 



111! 



20 



25 



30 35 

ALPHA CDEG3 



40 



45 



50 



55 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO ' BL 0.0 IN. 


WING SPAN ew = 7B.055 


FT. 


MOMENT REFERENCE 20 = U_ 375.0 IN. 


M.A.C. CU = 39.560 


FT. 




BOOY LENGTH LB - 1290.3 


IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 






SPEEDSRAKE 


NORMAL FOR 


CE I NCR. 






0.0 


0.00608 


0.00528 


0.00412 


0.00299 


0.00201 


0.00117 


. 00052 


15.000 


. 00243 


0.00215 


0.00165 


0.00120 


. 00080 


0.00047 


0.00021 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00267 


-0.00240 


-0.00181 


-0.00126 


-0.00075 


-0.00029 


0.00010 


45.000 


-0.00427 


-0 . 00365 


-0.00234 


-0.00240 


-0.00158 


-0.00100 


-0.00025 


55.000 


-0 . 00520 


-0 . 00430 


-0.00355 


-0-00308 


-0.00201 


-0.00162 


-0.00081 


70.000 


-0.00975 


-0 . 0074 1 


-0.00544 


-0.00376 


-0.00241 


-0.00139 


-0.00074 


87.200 


-0.01725 


-0.01275 


-0.00899 


-0.00569 


-0 . 00293 


-0.00075 


0.00081 



ENGINEER _—&£> 
OATE.jO : i^T£Z 



FIGURE 4.1.1.1-81 

EFFECT OF SPEEDBRAKE 



4.1.1.1-86 



«L* 



Rockwell International 

Space Division 



MACH NUMBER = 4.000 

• 02 i r | | | 1 | | | | I i | i | 



DELSB CDEGD 

50 100 






co 
en 



.02 



-.04 



-.05 



-.08 




I I I I I I I i 



till 



i i r 



! I I 



i i i i 



•■i-.'.-J 



I I 1 



I I t V 



I I ! I 



I I I I 



I I 1 I 



MM 



I. I l l 



I ] I I 



l l I 



! I I 



-10 



-5 



10 15 

ALPHA CDEG: 



20 



25 



30 



CONFIGURAT 


ION 




BASELINE ORB ITER VEHICLE 


REFERENCE DIfENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2630.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZP ■ U. 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 



ENGINEER 
CATE.jOrL3--— 'S 



FIGURE 4.1.1.1-32 

EFFECT OF SPEEDBRAKE 



35 











ALPHA 


COEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


DSRAKE NORM 


AL FORCE IM 


;r. 






0.0 


0.0OH37 


0.00255 


0.00150 


0.00143 


0.00135 


0.00127 


0.00117 


0.00106 


15.000 


. 00 1 75 


0.00102 


0.00060 


. 00057 


0.00054 


0.00050 


0.00046 


0.00042 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.001H7 


-0.00129 


-0.00110 


-0 . 00089 


-0 . 00072 


-0.00059 


-0.00050 


-0.00060 


45.000 


-0.00243 


-0.00199 


-0.00160 


-0.00126 


-0.00099 


-0 . 00082 


-0.00071 


-0.00044 


55.000 


-0.00463 


-0 . 00382 


-0.00310 


-0.00237 


-0.00173 


-0.00126 


-0 . 00099 


-0.00079 


70 . 000 


-0.01105 


-0.00990 


-0.00840 


-0.00620 


-0 . 00425 


-0.00300 


-0.00207 


-0.00107 


87 . 200 


-0.01937 


-0.01753 


-0.01500 


-0.01121 


-0.00783 


-0 . 0C538 


-0.00344 


-0 . 00255 



4.1.1.1-37 



O LJ i \ *- - C i . - C C 



C . fv'l 



* 



Rockwell International 

Space Division 



MACH NUMBER = 4.000 

,oa| I I I I I l l | I | | | | | | | | i i | | 



DELSB CDEG) 

50 100 



m 

o 
a 



.02 



-.04 



-.06 



1 I TT^. ~ 



^^^•ggF^^'^s^g^^ • y - " - Lv ^ 



-.08' I I I I I 1 



J...L 



I I I I 



15 



I I I 



20 



25 



I I I I I I I I 



TT 



III! 



30 35 HO 

ALPHA CDEG) 



45 



50 



55 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO ' BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOTENT REFERENCE ZP = ML 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


DELSB (DEG! 


F 


G 


H 


I 


J 


K 


L 






SPEEDBRAKE 


NORMAL FCR 


CE I NCR. 






0.0 


0.00127 


0.00117 


0.00106 


. 00095 


0.00060 


0.00006 


-0.00028 


15.000 


0.00050 


0.00046 


0.00042 


. 00037 


0.00024 


0.00004 


-0 . 000 1 1 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00059 


-0 . 00050 


-0.00060 


-0.00044 


-0.00022 


0.0 


0.0 


45.000 


-0.00082 


-0.00071 


-0.00044 


-0.00032 


-0.00013 


0.0 


0.0 


55.000 


-0.00126 


-0.00099 


-0 . 00079 


-0.00029 


0.00004 


0.00019 


0.0 


70.000 


-0.00300 


-0.00207 


-0.00107 


-0.00043 


0.00002 


. 00032 


0.0 


87.200 


-0.00538 


-0.00344 


-0.00255 


-0.00103 


-0.00034 


-0.00021 


0.0 



ENGINEER -£**£> 
DATE__LfcnLr35 



FIGURE 4.1.1.1-83 

EFFECT OF SPEEDBRAKE 



4.1.1.1-88 



a 



Rockwell International 
Space Division 



MACH NUMBER 



5. 000 



.oa 




m 
en 

CJ 

a 



-.OH 



-.06 



-.08 



i i i i I i i i i M I I I I I i I i I i j I I 



OELSB CDEG) 

50 100 

| I I ! i | > i i i 



if IT il 



1 I 1 I 



I. .I..J_L 



-L-.L. 1..1- 



I I I I 



I I f , I 



I I I 1 



i I I I I I I I "j 






I I ! I 



P-^-H 



^W 



-10 



to 

ALPHA 



15 

CDEGD 



20 



25 



30 



35 



COflGURAT 


'ON 




BASELINE CR9ITER VEHICLE 


REFERENCE Olr-tNSIOS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.055 


FT. 


MOTtNT REFERENCE 20 = WL 375.0 IN. 


M.A.C. CU ' 39.560 


FT. 




BCOY LENGTH LB ■ 1250.3 


IN. 











ALPHA 


(DEGl 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELSS !D£G) 


A 


8 


C 





E 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


. 00244 


0.002S2 


0.00220 


0.00103 


0.0 


0.0 


0.0 


0.0 


15.000 


0.00099 


0.001C6 


0.00090 


0.00042 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00107 


-0 . 00096 


-0.00080 


-0.00059 


-0.00042 


-0 . 00029 


-0.00020 


-0.00015 


45.000 


-0.00213 


-0.00190 


-0.00160 


-0.00118 


-0 . 00082 


-0.00069 


-0 . 00066 


-0.00033 


55. COO 


-0.00374 


-0.00318 


-0.00260 


-0.00190 


-0.00133 


-0.00110 


-0.00099 


-0.00048 


70.000 


-0 . 00720 


-0.00513 


-0 . 00500 


-0.00381 


-O.0C281 


-0.00203 


-0.00141 


-0.00064 


87.200 


-0.01499 


-0.01338 


-0.01150 


-0.00911 


-0.00685 


-0.00489 


-0.00341 


-0 . 00224 



ENGINEER £&& 
DATE __L9HKrDj& 



FIGURE 4.1.1.1-84, 
EFFECT OF SPEEDBRAKE 



4.1.1.1-89 



sdt: ; 



c ', 1 '^ r ■ 
o f t -- v. I ' 



M 



* 



Rockwell International 
Space Division 



MACH NUMBER 



.02 



o v r r r ^j-fa^gs^' ^^3*4?^- ^^--- '■*"*■ 



CD 

cn 

U 

a 



-.oa 



-.CM 



-.05 



-.08 



TH I 



5.000 

I I i l | I l I I I l I i i I I ii i 



DELSB CDEG] 

50 100 



I I I I 



-^G- rr — *- = *-i 1" zr 



I I I I 



I I I 



I I 



ct fc t .KL t< U 



15 



SO 



25 



I I ' I 



I I I I 



I I I i 



I I i 



'=-*fc^-"i-?T 



I I I 



I I I I 



ft — H. M - 



! I I ! 



30 



35 

ALPHA 



to 
CDEG3 



45 



50 



55 



60 



BASELINE OR3ITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MOENT REFERENCE ZC - ML 375.0 IN. 



AT ION 




REFERENCE DIMENSIONS 




WING AREA SW » 2690.00 


SQ.FT. 


WING SPAN BW » 78.056 


FT. 


M.A.C. CW » 39.560 


FT. 


BODY LENGTH LB - 12S0.3 


IN. 



DELSB (PEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



15.000 

F 



20 . 000 
G 



ALPHA (DEG) 



25.000 
H 



30 . 000 

I 



35.000 
J 



HO . 000 
K 



45.000 

L 



50.000 
M 



0.0 

0.0 

0.0 
-0.00029 
-0.00069 
-0. 001 10 
-0.00203 
-0.00489 



0.0 

0.0 

0.0 
-0.00020 
-0.00066 
-0.00099 
-0.00141 
-0.00341 



SFEEDBRAKE NORMAL FORCE [NCR. 



0.0 

0.0 

0.0 
-0.00015 
-0.00033 
-0.00048 
-0.00064 
-0 . 00224 



0.0 

0.0 

0.0 
-0.00017 
-0.00026 
-0.00025 
-0.00087 
-0.00190 



0.0 
0.0 
0.0 

-0 . 00008 
-0.00009 
-0.00007 
-0.00041 
-0.00097 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



ENGINEER Dlrh 



DATE. 



FIGURE 4.1.1.1-85 

EFFECT OF SPEEDBRAKE 



4.1.1.1-90 



a 



Rockwell International 

Space Division 



MACH NUMBER 



8.000 



DEL SB CDEGi 

50 100 



.02 



on 

(O 



-.OH 



.06 



-.08 



I I I l | I I I I | FT 



, "~r? .--_—-— r-^-.-.- .. 



■10 



"iii: n~n 



i i i i 



:r^T- 



i i i i 



J_JL_L_L 



^~ 



"■€- 



"-G--- 



-I I I! 



-i_L 



I I I I 



J --. . =^--^h 



10 

ALPHA 



15 

CDEG) 



20 



25 



30 



CONFIGURATION 






BASELINE ORB ITER VEHICLE 


REFERENCE 


Dll-CKSiCNS 




CENTER OF GRAVITY XO - F5 1076.7 IN. 


WING AREA 


SW = 2650.00 


SO. FT. 


OR Y0 = a. 0.0 IN. 


WING SPAN 


BW - 73.055 


FT. 


MOt NT REFERENCE 20 « WL 375.0 IN. 


M.A.C. 


CW = 39.550 


FT. 




BODY LENGTH 


LB = 1290.3 


IN. 











ALPHA 


(CEG1 








-10.000 


-5. 000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (DEG1 


A 


8 


C 


D 


E 


F 





H 






SPEE 


C3RAKE NORM 


AL FORCE IN 


Z7i. 






0.0 


0.00031 


0.00174 


0.00210 


. 00097 


0.0 


0.0 


0.0 


0.0 


15.000 


0.00012 


O.OC067 


. 00080 


0.00037 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00067 


-0.0CC54 


-0.00050 


-0 . 00040 


-0.00032 


-0 . 00029 


-0.00029 


-o.ccoie 


45.000 


-0.00185 


-0.00170 


-0.00150 


-0.00120 


-0.00094 


-0.00077 


-0 . 00065 


-0.0C0Z5 


55.000 


-0.00325 


-0 . 00294 


-0.00240 


-o.coie? 


-0.00143 


-0.00123 


-0.3CI 13 


-0 3GC5-. 


70.000 


-0.00591 


-0.00508 


-0.00420 


-0.00307 


-0.00219 


-0. 00164 


-0.00135 


-0.00079 


87 . 200 


-0.01132 


-0 . 00983 


-0.00830 


-0 00654 


-0.00475 


-0 . 00307 


-0.00190 


-0.00:7= 



ENCINEER^X»D 
OATE_„q r _£--I.£:r 



FIGURE 4. 1. 1. 1- 86 

EFFECT OF SPEEDBPAKE 



*. 1.1. 1-91 



Q r-. 



'.^ T . 



■CClC 



«L* 



Rockwell International 
Space Division 



MACH NUMBER 
•OSi-Trm ill! 



8.000 



DELSB CDEG) 

50 100 



<:— f^-F^.^r-^v^.y^-^^ fe-*~H-fi-W 



CD 
CO 

z 

8 



-.02 



.04 



■.C6 



i i i i 



i i i i i 



i i i i 



i i i i | i i i i 



-.08 



! I I I I I I I 



I I I I I I I I I M I I I I I I I I 1 I 



I I I I I I I 



¥. — M H- 



I I I 



15 20 25 30 35 40 

ALPHA CDEG: 



45 



50 



COfI 


gur; 


BASELINE CRSITER VEHICLE 




CENTER OF GRAVITY XO - FS 1073.7 


IN. 


OR YO = BL 0.0 


IN. 


MOMENT REFERENCE ZO = H. 375.0 


IN. 



REFERENCE DIMENSIONS 
WING AREA SU - 2630.00 SQ.FT. 
WING SPAN EW = 78.055 FT. 
M.A.C. CW - 39.550 FT. 

BOOY LENGTH LB * 1290.3 IN. 



55 



60 





ALPHA (DEG) 




15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELSB (DEG) 


F 


G 


H • 


I 


J 


K 


L 


M 






SPEE 


DBRAKE NORMAL FORCE IN 


CR. 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00029 


-0.00028 


-0.00018 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0.00077 


-0.00065 


-0 . 00036 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00123 


-0.00113 


-0 . 00054 


-0.00017 


-0.00005 


0.0 


0.0 


0.0 


70 . 000 


-0.00164 


-0.00135 


-0.00079 


-0 . 00035 


-0.00010 


0.0 


0.0 


0.0 


87.200 


-0.00307 


-0.00190 


-0.00175 


-0.00140 


-0.00067 


0.0 


0.0 


0.0 



engineerJX*^ 

DATE_J_Q--3--_!]£ 



FIGURE 4.1.1.1-87 

EFFECT OF SPEEDBRAKE 



KS 



4.1.1.1-92 



SD 



72 



SH-ceeo im 



'1* 



Rockwell International 
Space Ovteion 



NUMBER 



•PS| ITI I I | | I I I I I I | 



10.000 



DELSB CDEG) 

50 100 



* ■ A*ff »'g--""^%rlg2?r- 1 ^?jS 



CD 

en 
:z 



-.02 



-.OH 



.05 



-.08 



I i I I I I I I I 



vnw^jirirOxi 



W?w— l . 



Mil 



"i i n r 



Ml! I i i i 



[ I I 



ir^l--^----^-- 



JL_L 






I I I I 



MM 



I I I I 



I I I I 



I 1 I 



-10 



10 
ALPHA 



15 

CDEG) 



20 



25 



30 



25 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE Dir-ENSIONS 




CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.055 


FT. 


MOMENT REFERENCE ZO = U_ 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB = 12G0.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (DEG) 


A 


B 


c 





E 


F 


G 


H 






SPEE 


De?!AKE NORM 


AL FORCE IN 


:r. 






0.0 


0.00036 


0.00177 


0.00210 


0.00095 


0.0 


0.0 


0.0 


0.0 


15.000 


0.10014 


. 00068 


0.00080 


. 00036 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00051 


-0.00057 


-0.00050 


-0.00040 


-0.00033 


-0.00028 


-O . 00023 


-0. COO 14 


45.000 


-0.00170 


-0.00166 


-0.00150 


-0.00121 


-0.00096 


-0.00075 


-0 . 00056 


-0.00029 


55.000 


-0 . 002S8 


-0.00273 


-0.00240 


-0.00137 


-0.00143 


-0. 00114 


-0 . 00099 


-0 . 00042 


70 . 000 


-0.00525 


-0.00493 


-0 . 00420 


-0.00308 


-0.00220 


-0.00169 


-0.00145 


-0.00079 


87.200 


-0.01021 


-O.00S60 


-0.00830 


-0 . 00659 


-0.00489 


-0 . 00325 


-0.00211 


-0.00153 



ENGINEER Sy-^Z 
DATE„igZ£=LfTS 



FIGURE 4.1.1.1-88 

EFFECT GF SPEEDBRAKE 



4.1.1.1-93 



* 



Rockwell International 
Space Division 



MACH NUMBER = 10.000 

•°2ri I I i I i i I i I I i t i i i i I i | i r r i — r 



DELSB CDEG) 

50 100 

I I I I I I I i I 



fc — r r r^,^ ^^J-l^^^^^dsij^s^ J ^: ; j £^C^i^^C^K f .-ii Li(LilCL>l - H. *4- !« h . 



CD 

en 

z 
o 

Q 



.02 



.OH 



-.06 



.08 



n - ' r~r 



i i ' ' I I i I i 



M i I I i I l I I l l l 



_L_L 



i i i i n r 



h — M — M- 



i i i i i i i i i i i i ' .i 



15 20 25 30 35, HO 

ALPHA CDEG] 



45 



50 



55 



60 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE ZO « 14. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB ■ 1290.3 


IN. 





ALPHA (DEG) 




15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


H5.000 


50 . 000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEE 


DSRAKE NORMAL FORCE IN 


ZR. 






0.0 


0.0 


0.0 


0.0 . 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 ■ 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00028 


-0.00023 


-0.00014 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0.00075 


-0.00056 


-0.00029 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00114 


-0.00099 


-0 . 00042 


-0.00017 


-0.00005 


0.0 


0.0 


0.0 


70.000 


-0.00159 


-0.00145 


-0.00079 


-0.00035 


-0.00010 


0.0 


0.0 


0.0 


87.200 


-0 . 00326 


-0.00211 


-0.00163 


-0.00140 


-0.C0069 


0.0 


0.0 


0.0 



ENGINEER ^ __ 
QATE__.I&rZS55 



FIGURE 4.1.1.1-89 

EFFECT OF SPEEDBRAKE 



4.1.1.1-94 



CD 
CO 

o 
a 



r 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



DELSB CDEGD 

50 100 




.02 



-.04 



-.06 



-.08 



1 I I 



J_L 



l l l 



I. I l l 



I 1 I 



I l I I 



llli 



I, I I I , 



-10 



10 

ALPHA 



15 

CDEG3 



20 



25 



30 



35 





•X 


con - i guration 


BASELINE 0R8ITER VEHICLE 


REFERENCE OlfENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2S90.00 SQ.FT. 


OR YO » SL 0.0 IN. 


WING SPAN BW ' 78.056 FT. 


MCt-ENT REFERENCE ZO » UL 375.0 IN. 


M.A.C. CW « 39.560 FT. 




BODY LENGTH L8 = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0ELS8 iDEG) 


A 


8 


C 





E 


F 


G 


H 






. SPEE 


08RAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.00036 


0.00177 


0.00210 


0.00095 


0.0 


0.0 


0.0 


0.0 


15.000 


0.00014 


0.00C68 


0.00080 


. 00036 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00061 


-0 . 00057 


-0.00050 


-0.00040 


-0 . 00033 


-0.00028 


-0.00023 


-0.00014 


45.000 


-0.00170 


-0.00166 


-0.00150 


-0.00121 


-0.00096 


-0.00075 


-0.00056 


■ -0 . 00G28 


55.000 


-0 . 00288 


-0.00273 


-0.00240 


-0.00187 


-0.00143 


-0.00114 


-0.00099 


-0 . 00042 


70 . 000 


-0 . 00525 


-0.00493 


-0.00420 


-0 . 00308 


-0.00220 


-0.00169 


-0.00145 


-0. 00079 


87.200 


-0.0102! 


-0.00960 


-0.00830 


-0.00659 


-0 . 00469 


-0.00326 


-0.0021 1 


-0.00163 



ENGINEER. 
DATE JO* 



FIGURE 4.1.1.1-90 

EFFECT OF SPEEDBRAKE 



4.1.1.1-95 



SD 



H-CC6 IM 



* 



Rockwell International 

Space Division 



MACH NUMBER 
•051 l I I I 



i-ff+^^wv; '' V^^s^M^^^^iiH^^"^ ■' -r^' ^ - gKt. - fcrtr-3r-Ka-W:^ 



00 

8 



.02 



-.04 



-.05 



-.08 



15.000 

I i I l l i i i i i i i i i i i i 



DELSB CDEGD 

50 100 



n - i i i 



i i i i 



i i i 



i i 



i i i i 



i i i i | i i t i 
i i i i i i i i i 



* — H "+- 



J_ 



MM 



..i I 1 I 



15 



20 



25 



30 



35 

ALPHA 



40 

CDEG) 



45 



50 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - F5 1076.7 IN. 

OR YO * BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2630.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 
BCOY LENGTH LB » 1290.3 IN. 



55 



60 





ALPHA (DEG) 




15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEEDSRAKE NORMAL FORCE I NCR. 




0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00028 


-0 . 00023 


-0.00014 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0 . 00075 


-0.00056 


-0.00029 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00114 


-0.00099 


-0.00042 


-0.00017 


-0.00005 


0.0 


0.0 


0.0 


70.000 


-0.00169 


-0.00145 


-0 . 00079 


-0.00035 


-0.00010 


0.0 


0.0 


0.0 


97.200 


-0 . 00326 


-0.00211 


-0.00163 


-0.00140 


-0 . 00069 


0.0 


0.0 


0.0 



ENGINEER ±££> _ 
DATE._LQrXil5^ 



FIGURE 4.1.1.1-91 

EFFECT OF SPEEDBRAKE 



4.1.1.1-96 



* 



Rockwell International 

Space Division 



f-jACH, NUMBER = 20.000 
■P 2 i f | | | I I I I i I I i i i I i I I i ill 



DELSB CDEG) 

50 1 00 



, t. i iifl -) gL.~ 



-.02 



CD 
en 

u 
a 



-.05 



.08 




III. 



TT 



sT-.fciV-* "■ ~ 



Tl II Tl 



I I I I 



i I l 



I I I I 



I I I I 



I I I I 



_1_L 



J_ 



r^ — - 



J_L 



--,—r^. 



111' 



I I I I 



J_L 



-10 



10 15 

ALPHA CDEGD 



20 



25 



30 



35 



CONFIGURATION 


BASELINE 0RBITER VEHICLE 


REFERENCE Olt-eNSIONS 


CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOMENT REFERENCE ZO - U_ 375.0 IN. 


M.A.C. CM » 39.560 FT. 




BODY LENGTH LS » 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEGI 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


DBRAKE NORM 


AL FORCE IN 


CR. 






0.0 


0.00036 


0.00177 


0.00210 


. 00095 


0.0 


0.0 


0.0 


0.0 


15.000 


0.00014 


0.00063 


. 00080 


. 00036 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00061 


-0.00057 


-0 . 00050 


-0 . 00040 


-0.00033 


-0.00028 


-0 . 00023 


-0.00014 


45.000 


-0.00170 


-0.00165 


-0.00150 


-0.00121 


-0 . 00096 


-0.00075 


-0.00056 


-0.00029 


55.000 


-0 . 00298 


-0.00273 


-0 . 002H0 


-0.00187 


-0.00143 


-0.00114 


-0.00099 


-0.00C42 


70.000 


-0.00525 


-0 . 00493 


-0.00420 


-0.00308 


-0.00220 


-0.00169 


-0.00145 


-0.00079 


87 . 200 


-0.0102! 


-O.OCSSO 


-0 . 00830 


-0.00659 


-0 . G0489 


-0.00325 


-0.00211 


-0.00153 



ENGINEER^^ 1^ 
DATE._J_Q-?i--^B 



FIGURE 4.1.1.1-92 

EFFECT OF SPEEDBRAKE 



4.1.1.1-97 



SD72-S!i-CCc' I 



€> 



Rockwell International 

Space Division 



MACH NUMBER = 20. 000 

•o 5 ! I I I I 1" I I I I I i I 1 I I I I 



DELSB CDEG3 

50 100 



o ( : — r r r -~ 4 ^?r£g^ J ^"^' : v 1 -^^-"-'~ 



en 

CO 

z 
u 
a 



.02 



-.04 



.06 



.08 



I I I I 



_L_L 



-■♦Si^^^'^fci'----'--'*- 1 ^ ■*< LW. 1L< — t— j-K- M M . M 



-L I I I 



I I I I i t I I 



"TTT 



I I I I 



I I i I 



I 1 ! 



I 1 1 



I I I I 



15 



20 



25 



30 



35 

ALPHA 



40 

CDEGD 



45 



50 



CONFIGURATION 



BASELINE ORBITER CHICLE 

CENTER OF GRAVITY XO ■ FS 1076.7 IN. 

OR YO " BL 0.0 IN. 

MONtNTT REFERENCE 20 - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 



ENGIN£ER_£*iI> 
DATE__L9_rj5rr-£> 



FIGURE 4.1.1.1-93 

EFFECT OF SPEEDB.RAKE 



i I I I 
i l l I 



M — M M- 



55 



60 





ALPHA (DEG) 




15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


OELSB (C€G) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEE 


08RAKE NORMAL FORCE IN 


:r. 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00028 


-0 . 00023 


-0.00014 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0.00075 


-0 . 00056 


-0 . 00028 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00114 


-0.00099 


-0.00042 


-0.00017 


-0 . 00005 


0.0 


0.0 


0.0 


70 . 000 


-0.00169 


-0.00145 


-0.00079 


-0.00035 


-0.00010 


0.0 


0.0 


0.0 


87.200 


-0.00326 


-0.00211 


-0.00163 


-0.00140 


-0.00069 


0.0 


0.0 


0.0 



4.1.1.1-98 



KJ 



Space Systems Group 



«> 



Rockwell 
International 



-20 



ALPHA 





(DEG) 
ao 



o 
_j 

o 



.om 



.012 



.010 



.008 



.006 



.004 



.002 



.002 



-20 




40 60 80 

THETA CDEG) 



1UQ 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW = 78.056 FT 


MOTCNT REFERENCE ZO = WL 375.0 IN. 


M.AC CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











THETA 


(DEG) 








0.0 


1.000 


4.000 


10.000 


23.000 


53 000 


83 oca 


33.000 


ALPHA tOEG) 


A 


B 


C 


D 


E 


F 


G 


H 






LAND It* 


JG GEAR NORI* 


1AL FORCE CC 


EFFI 






-10.000 


0.0 


. 00064 


0.00214 


0.00348 


. 00563 


. 00857 


. 1 099 


0.01232 


-5.000 


0.0 


. 00045 


0.00154 


. 00250 


0.00404 


. 006 1 5 


. 00799 


. C'0Ss u 


0.0 


0.0 


0.00031 


. 00 1 02 


0.00166 


. 00269 


0.004 10 


0.00525 


0.00553 


5.000 


0.0 


. 00020 


0.00066 


0.00106 


0.00171 


. 0026 1 


0.00335 


0.00?75 


10.000 


0.0 


0.00011 


0.00039 


0.00063 


0.00101 


0.00154 


0.00197 


0:00221 


15.000 


0.0 


. 00004 


0.00014 


0.00022 


. 00034 


0.00053 


. 000S8 


0.0CC76 


20.000 


0.0 


-0.00003 


-0.00008 


-0.00013 


-0.00021 


-0.00032 


-0.0004! 


-0.00046 


25.000 


0.0 


0.00001 


0.00002 


0.00003 


0.00006 


0.00009 


0.000 1 1 


0.00012 



ENGINEER !>£•>£) 
3A1E "?;3Z'I_-J_'iI 



FIGURE 4.1.1.1-% 
LANDING GEAR NORMAL FORCE COEFFICIENT INCREMENT 



4.1.1.1-99 



SD72-SH-CCLC 1M 



* 



Rockwell International 
Spac* Division 




Landing Gear Down 



^ C N aio , 1NQ =C NG«0UN0" C NM«I 



'atouNo 

(MJCT 



SFHCT 



STREAM 




S,= -40.000 



s M =-n.7- 



ft 



<«,»•» 

<%•« 

({.»** 



575.M 



CONFIGURATION 

IlltimC JIIITM t€HICL£ 

CJNrit o* «*vir» ( t, »«» 1071.70 

o« 

HCmlHI UfltfKt 

lEFEHaCt OINHJIOIt 

JUUA W JIJO.OOO '•' 

ihn v.* 71.351 » 

mm .,» 315*0 h 

leor iixom i, • I2NJ04 . 



8 5i =ALL 



ACn, 



'08 




f„ h/b 

X, 1S06.S4 



J*L 



HflOMTX 
xf>AN 

h/b 




Angle of Aft 


oek, a ~» Degrees 






A -H.000 


s 0.0 


C H.000 


o 3.000 


t 12.000 


, 16.000 


G 20.000 




Increm 


antal Nor 


mal Force 


Coeffieii 


»nt , &Cn a 


»N0 »*«CT 


0.035 


-0.32480 


-0.14000 


0.08343 


0.12607 


0.19062 


0.28655 


0.37164 


0.050 ' 


-0. 25924 


-0.1 1810 


0.07243 


0.09493 


0.12470 


0.10494 


. 1 3964 


0.100 


-0.19079 


-0.07600 


0.03247 


. 06978 


. 09085 


0.09409 


0.10369 


0.200 


-0.09183 


-0.03880 


0.00947 


0.04010 


0.05632 


0.08984 


0.08217 


0.300 


-0.05063 


-0 . 02960 


0.00082 


. 02933 


0.04265 


0.06071 


0.08059 


O.SOO 


-0.02989 


-0.01 720 


0.00044 


0.01717 


0.02878 


0.03250 


0.04332 


1.000 


-0.01001 


-0.00500 


0.0 


0.00198 


. 004 1 2 


0.00618 


. 00820 


I.S00 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



ENGIN6!*- 

DATl ;?-/«- 77 

HgVtSEO: 



Figure 4.1.1.1-95 

GROUND EFFECT 



1. 6 



4.1.1.1-100 



•ft 



Rockwell International 
Spaca Division 




Landing Gear Oown 



AC N . 



^HOUNO 
SfMCT 



"^^r.artiifcin" ^NfUfj 



SfMCT 



S7SJAM 




5, = -30.000 



3„ = -11.7" 



CONFIGURATION 

USUIM JXI1TEI <CHICU 

ciNrn o* u«in / <,<•> I07J..1 

o< J % « u j.ao 

•oiMNr ihihmci li,i»i 17J.JQ 

UFtunct jwtMWH 

•■u k.'2l]IJdti>' 

ihk *,* rvsss K 

wot iiMorii \ % » IIJUOO .• 



S„=ALL 



£<=*, 



'08 




>., h/b 

X, 1506.S4 
I. 282.71 



J 



•Van 

h/b 


Angle of Attack, a — Degree* 


t, -M.000 


1 0.0 


C 4.000 


o a. aao 


{12.000 


, 18.000 


20.000 




Incremental Normal Pores 


CsefflCM 


int ,^C N| - 


»NO IFTtCT 


0. 023 


-0.28434 


-0.13500 


-0.08546 


-0.06069 


0.02267 


0.26788 


0.32295 


0.030 ' 


-0.23952 


-0.16330 


-0. 09166 


-0.07103 


-0.00047 


0.15903 


0.22115 


0.10O 


-0.17134 


-0.11 730 


-0.09671 


-0.07258 


-0.01859 


. 05422 


0.11294 


0.200 


•0.093SI 


-0.05340 


0.00083 


0.02400 


0.05700 


0.07782 


. 08365 


0.300 


-0.06001 


-0.022HO 


0.01118 


0.02352 


0.04119 


0.04775 


0.05582 


0.500 


-0.03051 


-0 . 00620 


0.00541 


0.01423 


0.02501 


0.02731 


. 03203 


1. 000 


-0.00705 


-0.00500 


0.0 


0.00198 


0.00391 


. 00632 


. 00820 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



»EVtS£D: 



Figure U,. 1.1.1- 96 

GROUND EFFECT 



1.8 



4.1.1.1-101 



SLJ72 



SK 



ccec im 



*f* 



Rockwell International 
Soace division 




Landing Gear Down 



A<=N, 



iouno"^ s 'o«ouno N»*es 
•rncr trrtcr strjam 




5.= -20.000 



5„ = -U.7« 



CONFIGURATION 

iiuuic mm* umii 

etMiu o» <3JtA»irr ,i,iii 1(71.79 

«o<mnt iihhki ' c.>«n J7S.J1J 

ACFCRCNCE OIMCMIMJ 

uu wilKlllh 1 

ihi) k»« rj.o5i * 

war iiwarM i, » I3MJM ;• 



^ 



S,.= ALL 



'« 



&C f 



•zt 





i„ h/b 

*, 1506.34 
Z« 292.71 



MBOHV 

h/b 


AngU of Attack, at — Degrees 




A -M .000 


, 0.0 


e h.qoo 


3 a.oco 


E 12.000 


, is. ooo ! 


G 20.000 




Incremental Normal Fores 


Ceeffici« 


int t ilCN<j» N0 !F*kt 


0. 025 


-0.40532 


-0.28000 


-0.19674 


0.00420 


. 1 0698 


0.24834 


0.32302 


0.020 ' 


-0.29492 


-0.22000 


-0.14722 


0.00034 


. 08669 


0.19223 


0.24961 


0.100 


-0.21372 


-0.16320 


-0.0923B 


-0.00338 


0.05038 


0.10873 


0.16087 


0.290 


-0.12707 


-0.08060 


-0.03819 


-0.01208 


0.01221 


. 04937 


0.08169 


0.300 


-0.08111 


-0. 04600 


-0.02427 


-O.0OS19 


0.00297 


0.02650 


0.04381 


0.300 


-0.04037 


-0.02300 


-0.01472 


-0.00060 


0.00073 


0.01337 


. 02702 


1.0 00 


-0.00999 


-0.00500 


-0.00399 


-0.00198 


0.0 


0.00192 


0.00470 


1.300 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



ENGINH*' 
OaTJ: /O- 
(EVISSO: 



M-7-) 



Figure 4.1.1.1-97 

GROUND EFFECT 



1.6 



4.1.1.1-102 



#Jt 



Rockwell International 
Spaca OivHion 




Landing G«or Oown 



EFMCT EfPECT ST*tAM 




CONFIGURATION 

uuLiX miitei umcu 

CINTII 0» SIMITT j I. ■'« ;0JI.73 

0* J '. " u -1.J0 

KOMinr untfHci I <,><•* 375.31 

uii w !5S«.JC« i.' 

S»M i-," "I. Oil •» 

■ic ...• :i.a»>, 

wot limit* i, » iJJ4.Z30 ■• 



8 8 = -15.000 



S„ = -U.7' 



5„=ALL 



AC CE 




t.6 



.„ h/b 

X, 1306.34 
Z. 282.71 



ENGINEER 
OATJ _/£ 
UEVISED: 






HEIGHT/ 
•$>AN 




Angle at Aft 


ack, ae ■— Degrees 






A -H.000 


s a.o 


c H.000 1 


3 a. 300 


{ 12.000 


, 16.000 


,-20.000 




Incremental Normal Poret 


Cceffiei* 


int , AC«g»no !*m<7 


0.323 


-0.40414 


1 

-0.27000 


-0.13727 


0.00381 


0.15552 


0.2S762 


. 32642 


0.050 ' 


-0.30312 


-0. 18050 


-0.10773 


0.00331 


0.12567 


0.21037 


0.25333 


3.100 


-0.21279 


-0.12330 


-0 . 15527 


. 00252 


0.0710V 


0.13238 


0.15932 


0.20(J 


-0.11782 


-0. 06520 


-0.02961 


0.00165 


0.03527 


. 0725 1 


0.08688 


0.300 


-0.07240 


-0.04130 


-0.01724 


0.00100 


0.02351 


0.05252 


O.C609I 


O.SOO 


•0 . 03699 


-0.01900 


-0 . 00525 


0.00045 


0.01250 


0.03865 


0.03319 


i .aaa 


-0.00798 


-0.00200 


-0.00100 


0.0 


0.00196 


. 00385 


. 00364 


1 .300 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



v^ 



Figure 4.1.1.1-96 1 

GROUND EFFECTS 



4.1". 1.1 -103 



S D 7 2 



GH-CCCC IM 



*f* 



Rockwell International 

Space Orvmon 




Landing Gear Oawn 



!FFSCT !FF!CT STMaM 




s. = -io. 000 



8„ = -lL7* 



fc 



CONFIGURATION 

HStUlC JMITM UKICLt 
Cixrii o» s«Ayirf 

o« 

uf{iexcc atMcnstais 

u.a »»«2.S».8tt'.' 

mm »,■ nasi h 

.t* .. • J1SH » 



=^Y 



!.■»» 1071.79 

. . T. a K 9.91 

■innNci ' t,*»» J7S.M 



5 U = ALL 



ACr*,, 




-.a 



1.8 



<^5 



f. r h/b 

X. 1306.34, 
Z, 282.71 



HtlOMJX' 
h/b 




Angle of Att 


ack, oc — Degrees 






A -M.00O ! 


, 0.0 


c H.000 


9-000 


s 12.000 


■ 18. 000 


(.20.000 




Incremental Nor 


mal Force 


Coefficu 


inr , AC«g 


UNO "FFlCr 


0.023 


-0.33366 


-0.22000 


-0.09764 


0.07747 


0.18372 


0.29495 


0.33956 


0.050 ' 


-0.29825 


-0.18780 


-0.06978 


0.06026 


0.14701 


0.23816 


0.2725B 


0.100 


-0.22275 


-0.13060 


-0. 04626 


0.03188 


. 09535 


0.15655 


0.18468 


0.200 


-0.12009 


-0 . 0638O 


-0.023V I 


0.01127 


. 04277 


0.07365 


0.09089 


0.300 


-0.07104 


-0 . 03630 


-0.01585 


0.01 181 


0.02108 


0.04571 


0. 05662 


0.500 


-0.03260 


-0.01530 


-0.00398 


0.00518 


a .oi ioi 


0.02641 


. 03384 


' 1.000 


-0.00709 


-0.00200 


0.00007 


0.0OCI4 


0.00119 


0.00234 


. 00350 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



■NG1NH1' 
3 ATI /* 
(EVI5C0: 



J 

77^7 



Figure 4.1.1.1-99 

GROUND EFFECT 



4.1.1.1-104. 



€* 



Rockwell International 

Seaca Divawn 




Landing G«ar Oown 



^ 



tFMCT 5FFICT STUSAM 



ACn,, 




= -5.000 



S„ = -L1.7- 



CONFIGURATION 

iiseukc amirEii ameiE 

CI»>H a* <3i»»irT , i. im 11)71.78 
01 ' % » u 3.30 

•MMNr unitHci Il,»k 37S.a« 
MFUCXH 3IMCMIMS 

aha wZSSS.OOSit' 

iiui •,• '1-354 •• 

«aC «.» JJ.JSJ h 



5 S1 = ALL 




f„ h/b 




h/b 



0.029 
0.350 ' 
3.100 
0.200 
0.300 

a. 300 

1.300 
1.500 



AngU of Attack, a — D«ar««i 



A -H.00O I, 0.0 



e ««.ooo j a a.aoQ j 8 ia.ooo |> is.ooo [ g 2o7ooo 



ncr»w«n«a) Normal Forc» Cc«ffici«nt , ACwquno jftjct 



-0.32278 
-0.23765 
-0.16836 
-0.107m 
-0.07376 
-0.03872 
-0.00606 
0.0 



-0.1 8500 
-0.15240 
-0 . 1 0430 
-0 . 05860 
-0.03760 
-0.01610 

0.0 

0.0 



-0.06805 
-0. 05726 
-0.02547 
-O.0OSS6 

-0. 00*440 
0.00190 
0.00003 
0.0 



0.10213 
. 07336 
0.04603 

0.02205 
0.015S2 
. 00862 
0.00304 
0.0 



OATJ /C 

itviseo- 



ML. 



0.22182 
0.18575 
0. 1 1 940 
0. 05^0 1 
. 02S67 
0.01590 
. 00705 
0.0 



0.3245B 

0.25966 
0.17373 
0.08949 
0.05397 
0.03133 
0.01C85 
0.0 



0.H1439 
0.30012 
0.19680 
0. 10464 
. 06556 
0.33950 
0.01666 
0.0 



V, 



F!g<jr» 4.1.1.1- 100 I 

GROUND EFFECT] 



4.1.1.1-105 



SE7 



-Si 



■CCCC IM 



€* 



Rockwell International 

So»c» Otvtawn 




Landing Gacr Down 



^ C N 9 , und ::Cn ciouno Cn '"! 



5,= 0.0 



^<J«OUNO 

jpmct 



JFftCT 



STUtAM 




5„ = -n.7« 



CONFIGURATION 

UUIUC 9IIITEI VCIIICLE 

ctNii* at GMimn i >-.•'* 1971.73 

•OlMNI linHKl 

ufchxci amtMioiJ 

mu w2fN.Mfi>' 

vuc v,» '1-051 N 

u< .. > JJ.58I » 






8 U =ALL 



^i 




Ur h/b 

X, 1506. JA 
Z, 282.71 



• 

M€IOMT^' 
•tFAN 

h/b 


Angle of Attack, ct — D«gr««« 




A -h.ooo 


s o.o j 


c H.OOO 


9 3.000 


5 12.000 


t 16.000 


a 20.000 




Incremental Normal Fore* C«effiei< 


mt , (ACnq 


UNO !FMCT 


0. 029 


-0. 18863 


-0.08500 


0.05136 


0.1663S 


0.25129 


0.29008 


0.31932 


0.030 ' 


-0.16753 


-0.07520 


. 04055 


0.13627 


0.20690 


0.25509 


0.27979 


0.100 


-0.1H121 


-0.05580 


0.02583 


. 09666 


. 1 3848 


0.17991 


0.20400 


0.23O 


-0.09073 


-0.03590 


0.01075 


. 04 1 34 


0.06514 


. 09354 


. 1 0974 


3.300 


-0.06121 


-0 . 02230 


0.00548 


. 022S6 


. 04502 


. 06332 


. 07383 


0.500 


-0.02259 


-0.01080 


0.00351 


0.01084 


. 02563 


0.02912 


0.03504 


1. 000 


-0.00495 


-0.00200 


-0.00014 


-0.00029 


0.00164' 


0.00371 


O.O 0564 


1.300 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



oat* M-/1-77 



v^ 



Figure k. 1.1.1- 1C1 

GROUND EFFECT 



1.6 



4.1.1.1 



JLU» 



'Jt 



Rockwell International 

SpacaOtvwton 




Landing Gear Oown 



^ C N 5 »cuH(f CN a*ouNo" C NfRei 

SPMCT EFHC7 ST«am 




5,= 5.000 



5„ = -U.7- 



fZ 



CONFIGURATION 

I1UIIIK MIITU fEKIClE 

cixm a» c*«ir» , t,'<» 1071.73 

ai ( T . « h 1.S0 

aaoiHf nrfiiHCi 'l,'-^ 17S.QJ 

nnum iimcmsioms 

<n> v.>2f!v.00f >•' 

sun >,' 'LOJi h 



MOT KNOTM 






5 5i = ALL 



.4 



±c» zi 



1 1 i 


1 1 1 


1 1 ( 


1 1 1 


1 1 1 


r t~ i 


1 1 ! 


i 1 


\ 














- 








• 




. 




1 1 1 

t 


- o/*"'""""'^ 












V 


- 


1 1 1 


III 


111 


1 1 1 


.1,. 1 1 


i i i 


1 1 1 


1 1 ' 



0.2 



0.4 



0.6 




0.3 
t„ h/b 

X, 1304.34 
Z.. 232.71 



1.0 



1.2 



1.4 



MIGHT 



SHT/ 
SZtAt 

h/b 



Angle of Alfaclc, Ct *"* Degreei 



A-H.flOO 



0.0 



c 4.000 



3 8.000 t 12.000 \f IS. 000 [ a 20.000 



Incremental Normal Force Coefficient . A^^ono »»»tcT 



0.025 
0.020 ' 

o.iao 

0.2Q0 

0.300 

0.5OO 

1.0 00 

1.S00 



-0.17233 
-0.15216 
-0.12156 
-0.07540 
-0.04720 
-0.01697 
-0.00399 
0.0 



-0.08000 
-0.06530 
-0.04020 
-0 . 02620 
-0.01830 
-0.00710 
-0.00200 
0.0 



0.10615 

o.caeis 

0.05973 

0.02329 

0.00358 

. 00242 

0.0 

0.0 



0.13106 
0.15055 
0.10256 
0.04436 
0.02019 
0.01064 
. 00 1 98 
0.0 






241C6 





29371 





32798 





21077 





25687 





28245 





14811 





13471 





20177 





06966 





09339 





1079! 





03793 





05323 





06357 





02271 





03460 





03834 





00587 





00961 





01129 





.0 















.*' 



3aTS /<g-/»- 77 
JEVISEO: 



V 



Figure U. 1.1. 1-102 

GROUND EFFECT 

'4 ."1. 1.1- 107 



1.6 



sct:' • SK-ccec 



^ 



Rockwell International 

Soaca Division 




Landing G*cr Down 



JJMCT SfMCT 



d C Nmh 

STIEam 




5, = 10-000 



•5„ = -11.7' 



^= 



CONFIGURATION 

iimum muTEi «emeu 

ciHm e» «»in 1 1««»» I07IJB 

9* ; % « w ).Q8 

MOtMHT IHIHWI 'u>»» UVJO 

UFEU»« OlMCXSIUJ 

uw w« 2594.441 ••' 

ut* v," "L05I * 

iu* ,„« JliH* 

■oar uxor* i t ' inUH ;« 



^ 



5 SI =ALL 



ACh, 



'« 




t.s 




f., h/b 

X. 1506.44 
Z. 282.71 



/VAN 

h/b 


Angle of Attack, Ct — D«grt«s 


A -H.000 


, 0.0 


c H.0OO 


3 3.000 


( 12.000 


r 18.000 


20.000 


lncr«m 


•ntal Nor 


mal Force 


Cc«ffici< 


mt ,AC«g 


»NQ !M?CT 


0.023 


-0.08254 


0.08000 


0.15582 


0.2202"+ 


0.25781 


0.28150 


0.31129 


0.W0 ' 


-0.07442 


0.06360 


0.12847 


0.18348 


0.22031 


0.25070 


0.27534 


0. 100 


-0.06412 


0. 03460 


0.08593 


0.12872 


0. 16570 


0.18388 


0.20714 


0.200 


-0.05183 


-0.00130 


0.03306 


0.06009 


0.08120 


0.09402 


. 1 1 084 


0.300 


-0.04526 


-0.01670 


0.00350 


. 02329 


0.02983 


0. OH 167 


0.05190 


0.500 


-0.03130 


-0.01520 


0.00387 


0.00986 


0.00952 


0.01548 


0.02083 


1 .000 


-0.01337 


-0.00800 


0.0 


0.0 


0; 00098 


0.00192 


0.00292 


1.S00 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



»«Vl3IO: 



Pigur» A.. 1.1. 1-103 

GROUND EFFECT 



4.1.1.1-108 



,Jl 



'i> 



Rockwell International 
Sqaem Divoton 




Landing Omar Dawn 



EFFECT EFFECT ST»Eam 



ACn,, -2 



-.1 




configuration 
huum mutei vehicle 

u-m ioii.to 

.08 



CIMTII Of <J*A».tT 
«W«)N1 MfltfNCI 



( », » ii o.oc 



v^= 



urcicxct umedsioi: 

aii* l. < 2158.001 •.' 

imm v.' "1.255 N 

>u< .„• 315(4 » 

WOT UHOTM I, • IJSQ-jOO . 



5,= 15.000 



a„ = -u. 



5 Si = ALL 



-III 


1 1 1 


i 1 1 


""11 1 


r i i 


i i : 


1 1 ! 


it ! 


v^\ 














- 


^ 


\ 




»«■ rBi-v.T'^.- 




i i i 


! 1 1 


I ! 1 


I 1 I 


,1.1 !„. 


1 1 1 


111 


i i i 



0.2 



0.4 



0.6 



0.8 



R«f*r«nc« Pom! 



t.o 



1.2 



1.4 



1.6 




0*T{ 



J' 



HEIGHT/ 


Angle of Attock.O! — Degrees 


A -M.0OO 


, 0.0 


c 4.000 


8.000 


j 12.000 


> 16.000 


c 20.000 




Incremental Nor 


mol Fore* 


Ccef f ici< 


* n ' . a^Njn N 5 !«MCT 


0.025 


0.07221 


0.12500 


0.18098 


0.22068 


0.24976 


0.27946 


. 29555 


0.030 ' 


0.03845 


0.10500 


0.14884 


0.18640 


0.21058 


0.23999 


0.24550 


0.100 


. 00658 


. 06640 


. 1 1 37 


. 1 3958 


0. 15870 


0. 18100 


0. 18431 


0.200 


-0.04734 


-0.00560 


0.02197 


. 05382 


0.07388 


. 08962 


0.09381 


0.300 


-0 . 06948 


-0.03980 


-0.01759 


0.00490 


. 02860 


. 02929 


0.03064 


0.500 


-0.03704 


-0.02480 


-0.01034 


. 00264 


0.01624 


0.01648 


0.01661 


1.000 


-0.00998 


-0.00600 


-0.00200 


0.0 


. 00293 


0.00577 


0.00940 


! .500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



*GINEE« : _ 

j UViSED- 



v^ 



Figure ^.l.l.l-10i 

GROUND EFFECT 



4.1.1.1-109 



f ' r 



I M 



* 



Rockwell International 
SpacaDlvWon 



I 



en 

z 



-50 



■100 



-150 



-200 



-250 
1X10 



lilt 


1 1 1 1 1 1 1 1 


1 1 1 1 1 1 1 1 


y 


_ 








- 






f 


- 






1 


- 






1 — 


_ 






' 


- 






- 


- 






- 


- 






— 


- 






: 


- 






- 


_ 






- 


~ 




1 ! 1 1 1 1 ! 1 


1 1 1 ! ! 1 ! r 


1 1 1 1 1 II 1 


1 1 1 1 1 1 1 1 



-07 



1X10 



■06 



1X10 



-05 



1X10 



-0M 



1X10 



-03 



PINF 


CPSI3 


*■ 


CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE 


DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA 


SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 


BW - 78.056 FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. 


CW - 39.560 FT. 




BCCY LENGTH 


LB - 1290.3 IN. 



PINF (PSD 


■ * N SO.r 
ll/n 


NORMAL FOR 


1.000E-07 


-225.660 


1 . 000E-O6 


-236.400 


l.OOOE-05 


-231.520 


3.000E-05 


-203.190 


1.000E-0H 


-107.450 


3.000E-04 


0.0 


4.500E-04 


0.0 


I.000E-03 


0.0 



ENGINEER 

OATE fflfc/j-S- 



FIGURE 4.1.1.1-105 
NORMAL FORCE SURFACE IMPINGEMENT. DOWN-FIRING 



4.1.1.1-110 






1 - \J v^ --/ ... 



a 



Rockwell International 

SpacaOvWon 



1.5 



O 
to 

Q 




1X10 



-03 



PINF CPSID 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
Of YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW =■ 2690. CO SQ.F1 
WING SPAN 8W = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB = 1290.3 IN. 



PINF (PSI) 


^ N /aSe ~ Vn-d.g 


5«<0 j 5,>o 


DE NORMAL FORCE 5 I , OF 


1.000E-07 


-I. 150 


0.0 


3.000E-07 


-I .210 


0.230 


1 . 000E-06 


-1 .270 


0.460 


I.0O0E-O5 


-I .040 


0.290 


3.000E-05 


-0.690 


0.230 


H.500E-05 


-0.M00 


1 .160 


6.300E-05 


0.0 


0.0 


1.000E-0*+ 


0.0 


0.0 


1.000E-03 


0.0 


0.0 



ENGINEER'__[y}^_ 



(DATE. 



^fc 



^. 



FIGURE 4.1.1.1-10 
ELEVCN NORMAL FORCE SURFACE IMPINGFKFN 



, DOWN-FIRING 



4.1.1.1-111 



'1* 



Rockwell International 
SpacaDJvMon 



IS) 

u. 




1X10 



1X10 



1X10 

PINF CPSI) 



1X10 



1X10 



-03 



CONFIGURATION 


BASELINE 0R81TER VEHICLE 


REFERENCE DI^NSICNS 


CENTER OF GRAVITY XO ■ FS 1075.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW ■ 79.056 FT. 


MCtCNT REFERENCE ZO - UL T75.0 IN. 


M.A.C. CW • 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 









PINT (PSD 


*"A6 n ~ "Vmd«, 




5w<o 


S„>0 




DSF NORMAL FORCE S! ,D 




1.000E-07 


-1.730 


1.730 










1 . 0OOE-06 


-1.790 


1.790 










1 . OOOE-05 


-1.960 


1.960 










3.000E-05 


-2.310 


2.310 










4 . 500E-05 


-2.990 


2.890 










S.300C-05 


-2.600 


2.500 










I . 0O0E-OW 


- 1 . 330 


1.330 










3.000E-04 


0.0 


0.0 










H.500E-04 


0.0 


0.0 




ENGINEER 
DATE., ^ 


& 




I . OOOE-03 


0.0 


0.0 


.OOWN-FIRING 


FIGURE 
BODYFLAP NORMAL 


4.1.1. 1-10? 
FORCE SURFACE IMPINGEMENT 


M 


i 













4.1.1.1-U2 



S r 



M 



^P Rockwell International 

Spac* Division 
I 



_) 
Q 



OJ/OINF 

.1 




30 35 

ALPHA CDEG3 



MO 



45 



50 



OJ/OINT 



ircr 

. 0050 
0.0100 

o . oaoo 

0.0300 
0.0400 
0.0500 
. 0600 
0.0700 

o . oaoo 

. 0900 
0. 1000 
0. I 100 
0.1200 
0.1300 
-Q.i4Qp 



A 



"TO 

-0.0059! 
-0.01022 
-0.01875 
-0 . 02708 
-0.03511 
-0.04272 
-0 . 04979 
-0.Q5621 
-0. 06 188 
-0.06667 
-0.07047 
-0.07318 
-0 . 07467 
-0.07467 
-0 - 07467 



i-(^j(jty^(f. 



Ti,r maiJ flow rate 

Vj= exit velocity 

fl = number of thrujrerj 



A,.,= 1ft* 
S,.,= 2690 ft 2 



"2c?. 500 
_B 



AJTffi A 



"tntr 

-0.004 04 
-0.CC303 
-0.01S31 
-0.02821 
-0.03705 
-0 . 04520 
-0.05250 
-0 . 0588 1 
-0 . 063SS 
■0.06781 
■0.0702: 
■0.07100 
■0.07100 
■0. 07 100 
•0.07100 



KGffMAL f-'C3(fg JTTT 



7773031 



"32.500 - 



TTTff 

-0.00307 
-0.00816 
-0.01S0S 
-0 . 0275.J 
-0.03638 
-0.04454 
-0.05167 
-0 . 05826 
-0.06359 
-0 . 06774 
-0.07060 
-0.07204 
-0.07195 
-0.07195 
-0-Q7tS5_ 



070 
-G. 004 05 
-0.00749 
-0.01523 
-0.02374 
-0.G3250 
-0.04102 
-0.04831 
-0 . 05534 
-0 . 06C 1 4 
-0.06269 
-0.06297 
-0.062S7 
-0.06297 
-0.05297 
-0 . 06297 






TO 

-0.00543 
.01005 
.01854 
. 02539 
.03330 
. 03=35 
. 0^455 
-0.0489! 
-0 . 052*2 
-0 . 05509 
-0 . 05690 
-0.05787 
-0 . 057&8 
-0.057=3 I 
-0 . 057=6 j 



*n„ ■*.**.(£) ♦*,(■&)'♦*.(■& 



ALPHA ( 



m 



17.500 
22.500 
27.500 
32.500 
3S-75Q 



-0.0015 
0.0010 
0.0021 

-0.0010 

-0.0CQ6 . 



*1 



-1 



E52TJ 

0100 

I .0400 

-0 . 5690 

-0-9970 



^^ 



0.4590 

1.1600 

-8.8000 

4.2400 



<V^) M ,JV^l 



25.2000 
19.7000 
83.4000 
0-0 



.0050 
0.0C5O 
. 0050 
0.0050 
0-0050 



U.lcOO 
0.1 100 
0. 1200 
. 0950 
0.120Q 



Interpolote for ari not 
ihown <yV*i calculation 
of given a'% only. 






OA" 



*p* 



!■* 



FIGURE 4. 1.1.1- ins 

NORMAL FORCE JET INTERACT? CM. DOWN-FIRING 



4.1.1.1- U3 



* 



Rockwell International 

Space Division 



A<N, 



.0 



-.02 



.04 



.06 



<***== 






. — — ^cfc,- \ -Jr S t I l/llll 

— : Bv-- '\ \ ' //•tin/ 

^.-rl— — «^>™ -A. \ ' , ' i in 



iiii 



I ! ,1 I 



' ' i 



'/// 



// 



J_L 



MJ/MINF 
.05 

I I ' ' ' I ' 

SS OCOCGGOOCCa S- 



.10 



I I 1 



10 



15 



20 



as 



30 



ex 



CDEGD 



35 



HO 



45 









oo 


(CiG) 








7.500 


12.500 


17.500 


22.500 


27.500 


32.500 


33.750 


Mj/Mir-r ■ a 


A 


8 


C 


O 


e 


F 


G 






nCRm 


At. FCFCE j| 


.£F 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


-0.00013 


-0.00055 


-0.C0039 


-0.0C002 


0.0 


0.0 


0.0 


0.005 


-0 . 00C57 


-0 . 00276 


-0.00IS5 


-0.00011 


0.0 


0.0 


0.0 


0.010 


-0 . C0463 


-0.00558 


-0.00383 


-0 . 00022 


0.0 


0.0 


0.0 


0.015 


-0 . 0CGS7 


-0.00845 


-0.0C518 


-0.00207 


0.0 


0.0 


0.0 


0.020 


-0.01220 


-0.01102 


-0.0102H 


-o.oossa 


0.0 


0.0 


0.0 


..0.025 


-0.01541 


-0.01359 


-0.01545 


-0..01312 


0.0 


0.0 


0.0 


0.030 


-0.01831 


-0.01594 


-0.02119 


-0 . 02042 


0.0 


0.0 « 


0.0 


0.035 


-0.02C89 


-0.01815 


-0.02534 


-0.02752 


0.0 


0.0 


0.0 


0.040 


-0.02316 


-0 . 02022 


-0.C3177 


-0.03377 


0.0 


0.0 


0.0 


0.045 


-0.02511 


-0.02214 


-0.C3537 


-0.03791 


0.0 


0.0 


0.0 


0.050 


-0.02675 


-0 . 02393 


-0.03702 


-0.03908 


0.0 


0.0 


0.0 


0.055 


-0.02307 


-0.02557 


-0.03702 


-0.03908 


0.0 


0.0 


0.0 


0.060 


-0 . 02908 


-0.02707 


-0.03702 


-0.03908 


0.0 


0.0 


0.0 


0.065 


-0.029C8 


-0.02707 


-0.03702 


-0.03=08 


0.0 


0.0 


0.0 


0.070 


-0 . 02908 


-0 . 02707 


• -0.037C2 


-0 . 039C3 


0.0 


0.0 


0.0 






-/ l v* 



■agrKf-X'^r-"-^*) 



'1 
», 3 txir v«(ocify — Fps 

9 t » nozzi* Waif angla at txir 



AC 



N 



'J I 



^O + A^ + ^fe) 2 ^ 3 ^ 



v Jl 



K J( =I.O 

Interpolate for Ct'% not 
shown ad'tei calculation, 
of given a'i only 



CAUTION: Polynomial curve-fit is valid CKLY for the mass flow ratio rar.re 
given in the above table. 



ALPHA (CEO) 


A0O3.MIN.MAX 




A 


Ai 


A 2 


*3 


eVnU. 


\ J An„4t»x 






NORMAL FORCE Jl ,SF 




7.500 


. 00330 


-0.32530 


6.28930 


0.0 


. 00500 


0.C5000 


ia.500 


0.00030 


-0.62550 


2.83930 


0.0 


0.00500 


0.05000 


17.500 


-0.00710 


0.96400 


-72.60001 


827.00000 


0.01000 


0.C5000 


22.500 


-0.00870 


1.85000 


-113.00000 


1277.00000 


0.010CO 


O.C5000 


27.500 


0.0 


0.0 


0.0 


0.0 


. 00500 


0.06000 


32.500 


0.0 


0.0 


0.0 


0.0 


0.00500 


0.05000 


38.750 


0.0 


0.0 


<?•<? 


0.0 ■ 


0.00500 


. C6000 



CNG 

OATE 



i«er IP FIGURE 4.1.1. 1-109 

E..^.m£" NORMAL FORCE JET INTERACTION. SIDE-- 1RING 



J 



K^ 



4.1.1.1-114 



c r 



a 



Rockwell International 

Spec* Division 

L 



OJ/OINF 
.1 

1 — r 



3 

-3 

•z. 
o 

Q 




30 35 

ALPHA CDEGD 





ALPHA (DEGi 


17.b00 


22.500 


27.500 


32.3G0 


38.750 


OJ/OII^ 


A 


B 


C 


O 


E 




nCKMal forcl Jl 


.1* 




0.0 


0.0 


0.0 


070 


0.0 


0.0 


. 0050 


-0.00004 


-0 . 00002 


0.0 


0.0 


0.0 


0.0100 


-0.00009 


-0.000C5 


0.0 


0.0 


0.0 


. 0200 


-0.00017 


-0.00010 


0.0 


0.0 


0.0 


0.0250 


-0.00191 


-0.00012 


0.0 


0.0 


0.0 


0.0300 


-0.00406 


-0 . 00233 


0.0 


0.0 


0.0 


0.0400 


-0 . 009=0 


-0-00764 


0.0 


o.o 


0.0) 


0.0500 


-0.01472 


-0.01333 


0.0 


0.0 


0.0 


. 0600 


-0.01980 


-0.01835 


0.0 


0.0 


0.0 


0.0700 


-0.02359 


-0.02172 


0.0 


0.0 


0.0 


. 0800 


-0.02523 


-0 . 0224 i 


0.0 


0.0 


0.0 


0.0900 


-0 . 02523 


-0 . 0224 1 


0.0 


0.0 


0.0 


0.1000 


-0 . 02523 


-0.02241 


0.0 


0.0 


0.0 


0.1100 


-0 . 02523 


-0 . 0224 1 


0.0 


0.0 


0.0 


0.1200 


-0.02523 


-0.02241 


0.0 


0.0 


0.0 


0.1300 


-0.02523 


-0 . 0224 1 


0.0 


0.0 


0.0 


0. 1^00 


-0 . 02523 


-0.02241 


0.Q 


0.0 


0.0 



*» \q A '.t/\2S. t< / V 0./ 



mj= mc»» flovo role 

VjS exil velocity 

n s number of thrujterj 



A r .,= lft* 
S„,= 2690 ft 2 



22.500 
27.500 
32.500 
38-750 



A 



k 1 



**„ -a * Ai (A.) +a 2 (A./.a 3 (A./ 



0.00G5 
0.0013 
0.0 
0.0 
JUL 



0.2880 
0.3900 
0.0 
0.0 
JUl 



- 1 8. yC00 141.0000 



(*A-lJ*'A-U 



-22.1000 

0.0 

0.0 

JUL 



169.0000 
0.0 
0.0 
JUL 



0.0200 
. 0250 
. 0050 
. 0050 
0-0050 



0.0500 
0.0800 
0.1200 
0.1200 
Q.lgOQ 



Interpolate 
jhown af{*\ 
of given a'j 



ror OC i no i 
calculation 
only. 



EfJGlNEEi 
OATE___ u „j 




^>- 



FIGURE 4.1.1.1-110 

NORMAL FORCE JET INTERACT ICN. UP-FIRING 



ii.1.1.1-115 



* 



Rockwell International 

Space, Dtvaion 

L 



DE REF CDEGD 



= -30.000 



LU 

o 



OJ/GINF 

A 

i i i i r~ 



.a 



i i i i 




25 30 35 

ALPHA CDEG] 



40 



45 



50 



OJ/OINT 




ALHHA (O.OI 


I'/.bUU 


B 


d/.bOO 

c 


32.500 
D 


38.750 

E 


Ot NOhMAL FORCE . 




0.0 


0.0 


0.0 


0.0 


o.o — 


0.0 


0.0050 


0.00033 


o.ooiea 


0.00291 


. 00042 


0.00179 


0.0100 


0.00077 


. 00337 


0.00566 


0.00120 


0.00340 


o.oaoo 


0.00192 


0.00671 


0.01062 


0.00360 


0.0061 1 


0.0300 


0.00335 


. 00997 


0.01476 


. 00670 


0.00812 


0.0400 


0.00494 


0.01259 


0.01796 


0.00999 


0.00943 


0.0500 


0.00558 


0.01503 


. 020 1 1 


0.01297 


0.01005 


0.0600 


o . ooa 1 6 


0.01573 


0.02109 


0.01515 


. 00997 


0.0700 


. 00955 


0.01764 


. 02077 


0.01602 


0.0CS20 


0.0800 


0.01065 


0.01762 


0.01905 


0.01508 


. 00773 


0.09C0 


0.01137 


0.01651 


0.01580 


0.01184 


0.00555 


0.1000 


0.01137 


0.01651 


0.01580 


0.01 184 


. 00556 


0.1100 


0.01137 


0.01651 


0.01580 


0.01 184 


0.00556 


0.1200 


0.01137 


0.01651 


0.01580 


0.01184 


. 00555 


0.1300 


0.01137 


0.01651 


0.01580 


0.01184 


. 00555 


0. 1400 


0.01137 


0.01651 


0.01580 


0.01184 


0.00555 



■t=(^..,)(lt)"= - 15 "(t) (.=„)■ -*.♦*.£.) ♦*,(■£•)'♦*,#-) 

5, = — 30° 
71.= man Flow rot« A. ■= 1 f|2 *SF 



Tij= maji Flow rote 

Vj= exit velocity 

n - number of thrusterj 



A f .,= lft 2 
S„,= 2690 ft 2 



Interpolate for Ot\ not 
shown a/t*% calculation 
of given a'l only. 



ALPHA (PEG) 



m.. 

22.500 
27.500 
32.500 
38-75Q 



A 



UTTT 
0.0 
0.0 
0.0 

JJJL 



M 



i* mfMrib 



^AXm (V*.U 



U.Ubib 
0.3340 
0.5970 
0.0439 
0-3750 



2.5000 
0.5660 

-2.9100 
8.4800 

-3-4800 



-25.1000 

-19.7000 

-83.4000 

Q,Q 



O.OObO 
0.0050 
0.0050 
. 0050 
0-0050 



0.0900 
0.0900 
0.09C0 
0.0900 

o-pgo? 



ENSINEER"^^ 

D ATE.jw»Tg§::: 



FIGURE 4.1.1.1-111 

ELEVON NORMAL FORCE JET INTERACTION. DOWN-FIRING 



4.1.1.1-11* 



* 



Rockwell International 
Spaca OKision 
l_ 



DE REF CDEG3 



10.000 



OJ/OINF 
.1 



UJ 

U 
Q 



-.005 



.010 



-.015 




,^ ^om Aw w&w 






/ / 



/ / / 



/ 



■ 1 1 1 1 1 1 1 1 1 



/ i / / / 1 i / 1 1 

i 1 1 1 / 1 1 1 / / 

i ///////// 
/ i / i i i i '/ 
1 1 1 1 1 1 1 1 / 

i / 1 1 1 / 1 1 ■ 

i ' i ' 1 1 1 1 1 



J I L_J_ 



////// 
/ / / / / 



OGOfCCpO l jHJPDpopOfi 



J_J L_J_ 




15 



20 



25 



30 35 

ALPHA COEG) 



HO 



45 



50 







ALFWA <DEG> 


l / . bOO 


22.500 


27.500 


32.500 


JS.TbO 


OJ/OINT 


A 


8 


c 


D 


E 




Cfc NCF^AL FCRCt o 


1 ,c c 




O.U 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0050 


-0.00085 


0.0 


0.0 


0.0 


0.0 


. 1 00 


-0.00166 


0.0 


0.0 


0.0 


0.0 


0.0200 


-0.00323 


0.0 


0.0 


0.0 


0.0 


0.0300 


-0.00482 


0.0 


0.0 


0.0 


0.0 


0.0400 


-0 . 00655 


0.0 


0.0 


0.0 


0.0 


. 0500 


-0.00852 


0.0 


0.0 


0.0 


n 


0.0600 


-0.01086 


0.0 


0.0 


0.0 


. 0700 


-0.01056 


0.0 


0.0 


0.0 


0.0 


0.0800 


-0.01 086 


0.0 


0.0 


0.0 


0.0 


. 0900 


-o.oioee 


0.0 


0.0 


0.0 


0.0 


0.1000 


-0.01086 


0.0 


0.0 


0.0 


0.0 


0.1100 


-0.01 086 


0.0 


0.0 


0.0 


0.0 


0.1200 


-0.01056 


0.0 


0.0 


0.0 


0.0 


0.1300 


-0.01086 


0.0 


0.0 


0.0 


0.0 


Q.|4QQ 


-0.01086 


0.0 


0.0 


0.0 


0.0 



x=(#.,)(it)"=°- I5 "(t) 



mjZ masj flow rote 

Vj= exit velocity 

n = number of Ihruiiers 



A,. f = lf|2 
S r ,,= 2690 ft 2 



<*>> 



6, 






ALPHA (DEG) 


A 


A, 


A 2 


A 3 


<V*J M1N 


I /9«Jm*x 


(Jt NC™«.AL FORCE. JI.CF 


17.500 
22.500 
27.500 
32.500 

?8,75Q 


0.0 
0.0 
0.0 
0.0 
0.0 


-0.1740 
0.0 
0.0 
0.0 

0.0 


1.0100 

0.0 

0.0 

0.0 

0.0 


-18.8000 
0.0 
0.0 
0.0 
Q.O 


a. 0050 

0.0050 
0.0050 
0.0050 
0.0050 


0.050CT 
. 0600 
0.0600 
. 0600 

Q-oggg 



Interpolate for <x'i not 
shown a/t*\ calculation 
of given at'* only. 






ENGINEER 
DATE..jjuZtV-T.^.. 



FIGURE 4.1.1.1-112 
ELEVGN NORMAL FORCE JET INTERACTION. DOWN-FIRING 



4.1.1.1-117 



c '- "■ 



Q U' 



}-: - c : 



M 



* 



Rockwell International 

Space Division 



Se WF ~CDEG3 

.02, 



-30.000 



MJ/MINF 
.05 



& C -M 




20 23 

cc cdeg: 









ex, (C 


SG> 








7.500 


12.500 


17.500 


22.500 


27.500 


32.500. 


33.750 


MJ/MI^ A 


A 


s 


C 





E 


F 


G 


de ncrmal rosce ji .sf 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


0.0 


-0.00008 


-0.00133 


-0.00170 


0.00011 


0.00030 


0.00026 


0.005 


0.0 


-0.00041 


-0.00679 


-0.00851 


0.00054 


0.00148 


0.00129 


0.010 


0.0 


-0.00102 


-0.01058 


-O.OI27e 


0.00010 


0.00181 


0.00147 


0.015 


0.0 


-0.00182 


-0.01198 


-0.01376 


-0.00133 


. 00099 


. 00057 


0.020 


0.0 


-0.00231 


-0.01198 


-0.01376 


-0.00374 


-0 . 00093 


-0.00143 


0.025 


0.0 


-0.00299 


-0.0! 193 


-0.01375 


-0.00714 


-0.00410 


-0.0C450 


0.030 


0.0 


-0.0053S 


-0.01198 


-0.01375 


-0.01152 


-0.00S37 


-0 . 00257 


0.035 


0.0 


-0.00693 


-0.011=3 


-0.01376 


-0.01689 


-0.01379 


-0.01393 


0.040 


0.0 


-0.00S69 


-0.01 1S3 


-0.01376 


-0.02334 


-0 . 02035 


-0.02023 


0.0^5 


0.0 


-0.01063 


-0.01193 


-0.01376 


-0 . 03058 


-0.02SC3 


-0 . 02772 


0.050 


0.0 


-0.01277 


-0.01193 


-0.01376 


-0.03S90 


-0 . 03535 


-0 . 03625 


0.055 


0.0 


-0.01277 


-0.01199 


-0.01376 


-0.03S90 


-0 . 03655 


-0 . 03625 


O.OSO 


0.0 


-0.01277 


-0.01198 


-0.01376 


-0.C3S30 


-0.03695 


-0 . 03625 


0.065 


0.0 


-0.01277 


-0.01193 


-0.01376 


-0.03S90 


-0 . 03595 


-0.03S25 


0.070 


0.0 


-0.01277 


-0.0! 199 


-0 . 1 376 


-0 . 03390 


-0 . 03595 


-0.03625 



h 



•ftTOHf-"'-"^*) 



Vj = exit velocity — fpi 

v M s freestream velocity — fpi 

9, ~ nozzii half angle at exit 



AC, 



'«REF 



-'.-.&MTWW&' 



*j, 



ALPHA (OEG) 


A0O3.MIN.MAX 


A 


A, 


Aj 


A 3 


^UFVLU 


OE NCRMAL FORCE Jl .SF 


7.500 


0.0 


0.0 


0.0 


0.0 


0.00500 


0.05000 


12.500 


0.0 


-0.06370 


-3.83510 


0.0 


. 00500 


0.05000 


17.500 


0.0 


-1.70000 


72.50000 


-827.00000 


0.005CO 


0.01500 


22.500 


0.0 


-2. 19000 


104.00000- 


1277.00000 


. 00500 


0.01500 


27.500 


0.0 


0.20700 


-19.70000 


0.0 


0. 00500 


0.05000 


32.500 


0.0 


0.41100 


-23.00000 


0.0 


0.00500 


. G5000 


38.750 


,,,0-P , 


0.36500 


-21 .80000 


0.0 


0.00500 


. C5000 



K J4 =LO 



Interpolate For (X s not 
shown af/et calculation, 
of given a's only 



CAUTION: Polynomial curve-fit is valid ONLY for the mass flow ratio ranee 
ftiven in the above taole. 
ENGli*ER hP FIGURE 4.1.1.1-113 

DATE...yrg77: < [: ELEVON NORMAL FQPCE JET INFRACTION. SIDE-FIRING 



^.1.1.1-118 



* 



Rockwell International 

Space Division 



K„ 



-.06 
.03 
.10 



be^-iDEG) = 10.000 ^ 



MJ/MINF 
.05 



'III! 



I'll 



( l I 



I'll 






10 



15 



20 25 

^ CDEGD 



30 



35 



M0 



45 









ct <C€G) 








7.500 


12.500 


17.500 


22.500 


27.500 


32.500 


33.750 


MJ/MINF A 


A 


B 


C 





E 


F 


G 






CE N33MAL FORCE J 


I.SF 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


-0.00019 


-0.00057 


-0.00183 


-0.00229 


-0.00057 


-0.00112 


-0 . 0CC29 


0.005 


-0 . 00097 


-0.00237 


-0.00938 


-0.01143 


-0.00287 


-0.00562 


-0.001^7 


0.010 


-0 . 00203 


-0.00555 


-0.01555 


-0.01848 


-0.00651 


-0.01180 


-0.004 15 


0.015 


-0.00317 


-0 . 0OSC6 


-0.01911 


-0.02208 


-0.01121 


-0.01552 


-0.00507 


0.020 


-0.0C44I 


-0.01037 


-0 . 02070 


-0.02322 


-0.01668 


-0.02590 


-0.01 320 


0.025 


-0.00574 


-0.01249 


-0 . 02092 


-0.02283 


-0.02301 


-0.03352 


-0.018=5 


0.030 


-0.00716 


-0.01442 


-0.02092 


-0.02283 


-0.03021 


-0 ."04200 


-0.02712 


0.035 


-0.0CS67 


-0.01617 


-0.02092 


' -0.02293 


-0.03627 


-0 . 05092 


-0.03591 


0.040 


-0.01027 


-0.01773 


-0.02092 


-0 . 02283 


-0.04720 


-0.05040 


-0 . C45S2 


0.045 


-0.01196 


-0.01910 


-0 . 02092 


-0.02283 


-0.05699 


-0. 070U2 


-0.05715 


0.050 


-0.01374 


-0.02029 


-0. 02092 


-0.02283 


-0.06765 


-0.08100 


-0.CS9S0 


0.055 


-0.0137V 


-0.02029 


-0.02092 


-0 . 02293 


-0.06765 


-0.08100 


-0.0695C 


0.060 


-0.01374 


-0.02029 


-0 . 02092 


-0.02283 


-0.06755 


-0.08100 


-0.0695." 


0.C65 


-0.01374 


-0 . 02029 


-0.02092 


-0.02283 


-0.06765 


-0. 03100 


-0 . 059SC 


0.070 


-0.01374 


-0.02029 


-0 . 02092 


-0 . 02=83 


-0 . 06765 


-0 . 09 1 00 


-0.C5S=: 



\h 



T„--m(f)^ e; f=>-^°-'(& 



Vj s axil velocity — fpi 

v a = fr»«jtr«am v«loeity~fps 

dj = nozzU half angl« at exit 



.10 




*&SiL =*o-,(4^A S (^A 3 (|y 



*ji 



ALPHA (OEG) 




A0C3.MIN.MAX 


Ao 


A, 


A 2 


A 3 


^AJCVLU 


PF NTKVAI Pnfire 1 . i, «• 




7.500 


0.0 


-0.18450 


-1.80710 


0.0 


0.00500 


0.050C0 


I2.5D0 


0.0 


-0.59330 


3.75160 


0.0 


0.00500 


0.05000 


17.500 


0.0 


-2.24000 


76.80000 


-827.00000 


. 00500 


02500 


22.500 


0.0 


-2.79000 


107.00000i 


1277.00000 


. 00500 


0.025C0 


27.500 


0.0 


-0.48800 


-17.30000 


0.0 


0.00500 


0.050C0 


32.500 


0.0 


-1.07000 


-11.00000 


0.0 


. 00500 


0.0500C 


38. "750 


0.0 


-0.17200 


-24.39999 


0.0 


. 00500 


0.050CO 



K^rl.O 



Interpolate ror a't not 
shown «y/«., calculation, 
of given a'% only 



CAUTION: Polynomial curve-fit is valid ONLY for the mass fl w ratio range 
given in the above table. 

engineer hP FIGURE 4. 1 . 1 . • - 1U 

QATE...din:i^ . ELEVON NORMAL FCRCE -JET INTERACT !CN. SttE-FIE ;>iG 

4.1.1.1-219 



PW Rockwell International 

Space Division 

L_ 



DBF REFCDEG3 = -14.250 



OJ/OINF 
.1 



-3 

00 

z 
u 

Q 




30 35 

ALPHA CDEGD 





ALPHA (DEG1 


17.50u 


22 . 500 


27.500 


32.500 


3b. /5G 


OJ/OISF 


A 


B 


C 





E 




cfir nc 


R.-iAl fOSCZ 


Jl.Cf- v 




0.0 


0.0 


0.0 


0.0 


LJ.U 


U.U 


. 0050 


-0 . 00282 


-0 . 00233 


-0.00184 


-0.00374 


-o . ou~oe 


0.0100 


-0.00529 


-0. 00^95 


-0 . 00354 


-0.00692 


-0.0042Q 


. 0200 


-0.00S29 


-0 . 00B73 


-0.00664 


-0.01 191 


-0.00857 


0.0300 


-0.0121! 


-0.01149 


-0.00940 


-0.01545 


-0.01311 


. 0400 


-0.01386 


-0.01339 


-0.01 134 


-0.01634 


-0.01 793 


0.0500 


-0.01413 


-0.CI372 


-0.01439 


-0.01634 


-0 . 02272 


. 0600 


-0.01413 


-0.01372 


-0.016S6 


-0.01634 


-0 . 0277c 


0.0700 


-0.01413 


-0.01372 


-0.01856 


-0.0163-. 


-0 . 03302 


0.0800 


-0.01413 


-0.0137? 


-0.01855 


-0.01634 


-0 . 03644 


. 0900 


-0.01413 


-0.01372 


-0.01S6S 


-0.01634 


-0.04299 


O.I000 


-0.01413 


-0.01372 


-0.01866 


-0.01634 


-0 . 04289 


O. 1100 


-0.01413 


-0.01 372 


-o.oiees 


-0.01634 


-0 . 04299 


0.1200 


-0.01413 


-0.01372 


-0.01666 


-0.01634 


-0 . 042S3 


0.1300 


-0.01413 


-C . 1 372 


-0.0ie66 


-0.01634 


-0.04269 


g.iugg 


-0.01413 


-0.01372 


-o.oiees 


-0.01534 


-0.042=9 



£=(t*.,H^:)" =0 - 15 * 3( t) 

A f .,= lf|2 



Bij= mass flow rote 

¥j= exit velocity 

n = number of thrusters 



A C N S = A 0L +A 1 



&) 



+ A- 




+ A- 



/<t> 



w 



S r .,= 269Gh< 



Interpolate for Ot'j not 
shown <y7>» calculation 
of given a'» only. 



ALPHA 



(C£G 

7500" 



T7 

22.500 
27.500 
32.500 
36.750 



Ao 



o.o 
o.o 
o.o 

JL0_ 



-0.5530 
-0.55B0 
-0.3810 
-0.8060 
-0-4110 



tgr 



^of*td^S5 



(V^l IN (*44 



'MM 



6.5900 

2.8500 

12.2000 

-0-B680 



-25.2000 
-19.7000 
-83.4000 
0-0 



O.OObO 
. 0050 
0.0050 
. 0050 
. 0050 



0.0424 
0.0423 
. 0570 
0.0331 

o.cseo 



ENG!f£ER 




FIGURE 4.1.1.1-115 
BGDYFLAP NORMAL FORCE JET INTERACTION. DOWN-FIRING 



4.1.1.1-120 



sli: 



- C C f C I iVl 



* 



Rockwell International 

SpmUvtoon 






O 

u 

I— I 
•"3 

z 



• u 


"l I I I 


1 1 I 


1 1 1 


'IT T" 


i i r 


1 1 1 


I 1 ! 1 


ill' 


III" 


1 1 1 


111 


1 1 I" 


- f» 


- 






















- 


- 3 
























~" 










^jrrrf?' 


• - 








A 






~" 


- «♦ 








-.9 


1 1 1 


1 1 I 


.III 


_L 1 I 


. ! 1 l._. 


_,L,i ,1 


I I I 


1 1 1 


1 1 1 


1 1 1 


1 1 1 


- 



16I8 20222H262830323H 

ALPHA CDEG) 



38 



CONFIGURATION 



BASELINE CRBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCtCNT REFERENCE Z0 - W. 375.0 IN. 



REFERENCE D^NSICNS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BU - 78.056 FT. 
M.A.C. CW » 39.560 FT. 

8CQY LENGTH LB - 1290.3 IN. 



<?C N)I 



a (*/*-) 



— ** if down firing j«( group is 
inoperative on on* side. 



ALPHA (C€G) 


<?CNj, 


*(V*J 


NORMAL FOR 


17.500 
22.500 
27.500 
32.500 
38.750 


-0.44000 
-0.40000 
-0.36000 
-0.3m 000 
-0.38000 



&H[(tk(tl] 

.<(*4<o.o: 



40 







ENGINEERN44; FIGURE 4.1.1.1-116 

am„_S.fjg/JJ NORMAL FORCE JET INTERACTION CARRYOVER. DOWN-PI RING 



4.1.1.1-121 



2::!^. -^M-CCCC 1M 



* 



Rockwell International 

Space Division 




AXIAL FORCE COEFFICIENT. The Orbiter Vehicle aerodynamic 
axial force coefficient is defined in this section. The basic 
aerodynamic axial force coefficient 
data are presented in three forms: 
1) as a function of angle of attack 
and Mach number from M = 0.25 
phrough M ■ 20; 2) as a function 
of anqle of attack and the viscous — 

3 . .. !ui\c RELATIVE WINO 

interaction parameter (ViJ from 
0.005 (equivalent to M = 13.6) 

through 0.08 (equivalent to 300,000 feet of altitude); and 3) as 
a function of angle of attack and altitude from 300,000 feet to 
600,000 feet. Orbital aerodynami c .characteristics are included 
in Appendix C. RCS jet thrust, thrust impingement, and flow field • 
changes due to jet plumes are also included in this section 
[k.\.\.2[. Uncertainties associated with the axial force charac- 
teristics are available in Section 6.0. 

The RCS flow field interaction data are presented as a contribution 
to the axial force (A) rather than the coefficient (Ca) since the 
terms due to jet thrust and impingement are independent of dynamic 
pressure and cannot, therefore, be normalized in the conventional 
manner. CAUTION should be observed when applying these terms In the 
flight regime where the RCS is used in conjunction with the aerody- 
namic force (df. Section 3.6); i.e., the aerodynamic coefficient must 
be converted to a dimensional force before adding the RCS flow field 
interaction effect (see also Appendix B) . 

The total axial force is: 

A ■ qS C. + A RCS 
total ^ Atotai rcs 

AERO 

"The total aerodynamic axial force coefficient is obtained by the 
following equation: 

C, - C. + [AC. + AC Ieuvo.* AC a + AC A + AC A 

Atotai a basic m elevator "aileron *body "rjooer "speeo 

A C K^^ rlA ' BK«^t 

+ AC + AC + AC + AC 

"FLEX "LANUING "GROUND "SRTS 

GEAR EFFECT POO 

where, 

C - Basic, full-scale, freestream, rigid (Figures A. 1.1. 2-1 
A 3asic body axial force coefficient through -6) 

NOTE: 1) All control surfaces neutral 

except 6 S8 - 25° . 

AC. ■ Change in axial force coefficient due (Figures 4.1.1.2-7 
a elevator Co elevon (elevator)- deflection, 6 e . through -36) 



•-•Refer to Appendix D when using digitized data. 

i*. 1.1. 2-1 



SD72-SK-CU(. I 



* 



Rockwell International 

Space Division 



AC Aa U ,, q „" Chan 9 e in axial force coefficient due 
UHON to aileron deflection, 6 a . 

" * (AC A + * C A > * iC A 

1 * 'R ' *T«im 

AC A,oo» " C j! n h*w ,n *? X "i I? r " coefflc,e « d« (Figures A. 1.1. 2-37 
to body flap deflection, 5„. through -65) 

AC A, U00 „ " **"%*" "'J' fo r« ^cient due (Assume zero) 

to rudder deflection, 6 

ACa S p» b " C J a " 9e '" ? xial force coefficient due (Figures A.I.J. 2-66 
•.*« to speed brake deflection, 6 J§ . through -92) 

4C A HB " chan 9<* in axial force coefficient due 
to aeroelastic deformation. 

- AC. cos a - AC. sin a 

where, AC . flexible lift incre- (cf.. Section 4,1 .2. 1 ) 
" ment 

AC D« t , " flexib, e drag incre- (cf.. Section 4,1.2.2) 
l " ment 

iC A lAN0(NG " C ^ n f.! n axial force coefficient due (Figure 4.1. 1. 2-93) 
ctAi to fully extended landing gear. 

NOTE: J. See Section 4.1.2.2 for land- 
ing gear drag during deploy- 
ment. 

ACa o«o b" Change in axial force "efficient due (Figures 4.1.1.2-94 
t?nZ? t0 proximity of ground, f(h/b) through -ICQ) 

NOTE: 1. See Section 3.4 for ground 

clearance and scrape attitude. 

AC. - Change in axial force coefficient due 

; L S S to addition of SILTS pod. 

- d.C n cos o -AC. sin a , A/ - 

u 5'lis I-5.U5 ^ dC l-5iiTs" cf Section 4.1.2.1) 

(AC D 5 s " T S s -cf Section 4.L2.2) 

RCS flow field interactions have been subdivided into three compon- 
ents: 

1. RCS JET THRUST (subscript JT) 

2. RCS JET PLUME IMPINGEMENT (subscript IMP) 

3. RCS JET PLUME EFFECT ON FLOW FIELD (subscript Jl) 



4.1 .1.2-2 



SD72-SH-CCeC 1M 



* 



Rockwell International 

Space Division 



The effect of the RCS may be described as a dimensional axial force 
(pounds) in terms of the significant contributing elements by: 

A «c$ " A jt + [A SutF + AA, + AA ],„,+ q S [AC + AC. + AC A 

'OOY M "(IJVON Aiody 

+ AC ]„ 

" DOWN 



where, 



IM' 



MIInO 
CaHyOvM 
2 SIDES 



a jt " Axial force resulting from number (n) (cf. Appendix B) 

of jets being fired (Reference data 
only) . 

- £ [A JI? n] - lb 

OJC 

NOTE: 1. OJG - operating Jet group 

2. Values given in Figure B-l are 
for reference only. 

A 5U «F " Axial force resulting from jet imp! nge- (Figure 4. 1 . 1 .2-104) 

"*' ment on Orbiter Vehicle surface(s). 

- 2^ [A 5u „' n ] - lb 
OJC im> 

A i:evoN ■ Change in axial force due 'to effect of (Figure 4.1.1. 2-105) 
IM ' impingement on eleven effectiveness. 

- Z [|r- 5 • n ] - lb 
ojc oo e 

e 

A«oor " Change in axial force due to effect of (Figure 4.1.1.2-106) 

Ft *' impingement on body flap effect i vene-ss . 



£ l ^r fi » * n ] ~ ,b 



OjG 

AC A - Change in axial force coefficient due (Figures 4.1.1.2-107 

" to jet interaction. through -109) 



Luc ] 

OjC "J> 



4.1.1 .2-3 



«L* 



Rockwell International 

Space Division 



AC 



Jl 



Change In axial force coefficient due 
to jet interaction effect on elevon 
effectiveness . 
r it \°^ 5 t 



<4 SA 



OJC 



'««' \ e, ff > 



NOTE: 1. Down-firing jets 

6„ < 0°, 6 
e e,. 



-30° 



5 > 0°, 6 - +10° 



(Figure h. 1.1. 2-110) 
(No effect) 



2. Side-f i ring jets 

- -30" 



<5„ < 0°, 6 
e e. 



6 > 0°, 6 
e e,„ 



+ 10° 



(Figure A. 1.1 .2-111) 
(Figure A. 1.1. 2-112) 



AC, 



HAP 



AC, 



3. Up-f I ring jets 

Change in axial force coefficient due 
to jet interaction effect on body flap 
effectiveness. 



(No effect) 
(No effect) 



, BOWN 
FIIING 
C*««tCvf» 
Jl 
2 SIDES 



= y ( ac a ) s (JilJ- 



Effect of carry-Over between left- and(Figure h. 1 . 1 .2-113) 
right-down-firing jet groups due to 
jet interaction. 



3 c A Jt 



WJ7$J 



[<*./*JJ 



NOTE: 1. $./<?„ - (0.15^3/qJ" 
J 

2. This term is zero when down- 
firing jet group is inopera- 
tive on one s ide. 

where: < (+./;J < 0.03 



A.1.1.2-A 



SD72-SH-CCCC 1M 



'1* 



Rockwell International 

Space Owion 







0.8 

NUMBER 



1.4 



CONFIGURATION 



BASELINE 0R9ITER CHICLE 

CENTER OT GRAVITY XO ■ FS 1075.7 IN 

OR YO " BL 0.0 IN. 

MOMENT REFERENCE ZO - W. 375.0 IN. 



REFERENCE Dl^NSIONS 
UJNG AREA SU * 2690.00 SO. FT. 
UIN3 SPAN 8W * 78.055 FT. 
M.A.C. CW - 39.560 FT. 

_KC V-LENGTH LB = 1290.3 IN. 



' ^ ."ha (PEG) 



I-' 



-10.000 

-5 . 000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30 . 000 

35.000 

40.000 

^5.000 

50 -POP 



0.250 

A 



0.400 

_J 



0.600 

c 



o.aoo 



MACK NU-BECj 



0.850 



0.02520 

0.05510 

0.06500 

0.05740 

. 064 1 

0.05490 

0.041 10 

0.02430 

. 00670 

-0.01210 

-0.03000 

-0 . 04230 

-0 . 04550 

-0.04780 



0.02S20 

. 05700 

0.0S550 

0.06610 

0.06470 

0.05550 

. 04200 

0.02520 

0.00730 

-0.01100 

-0.02820 

-0.04030 

-0 . 04530 

-0 . 04500 



0.04 120 
0.05940 
. 06760 
. 07020 
0.06690 
. 05760 
0.04390 
0.02720 
0.01180 
0.00730 
0.01340 
0.01620 
0.01620 
0.01520 



AXIAL FORCE COEFFICIENT 



0.900 

F 



0.920 

_S 



0.950 
H 



0.930 
I 



0.06490 
. 07060 
0.0>S0 
0.07630 
. 07280 
0.06500 
0.05780 
0.05290 
0.05180 
0.05350 
0.05630 
. 05970 
. 06370 
. 068C0 



07400 
07780 
08010 
08100 
07820 
07200 
06740 
06500 
06590 
06780 
07040 
07370 
07760 
08190 



0.08810 
0.08770 
0.08980 
. 09070 
0.08990 
0.08760 
0.08410 
0.08170 
0.08240 
0.08460 
0.08710 
0.08990 
. 09270 
. 09570 



O.OSShO 
0.09450 
0.09760 
0.09900 
0.09940 
0.09590 
0.09120 
0.08930 
0.08990 
0.09120 
0.09400 
0.09620 
0.09690 
0.10180 



0. 11200 
0. 11040 
0.11320 
0.1 1450 
0.11320 
0.10990 
0.10500 
0.10280 
0.10240 
0.10320 
. 1 0470 
0.1C670 
0.10900 
0.1 1150 



0.13450 
0. 13600 
13580 
13V60 
13220 
. 1 3070 
12980 
12960 
12950 
1 2960 
13030 
13160 
0.1 3340 
0. 13510 



0. 
0. 
0. 
0. 
0. 
0. 
0. 
0. 
0. 
0. 



D<?lNE£R-i2SX> 

o^E..io5:f^eI 



FIGURE 4. 1. 1.2 -1 
BASIC AXIAL FORCE COEFF I C I ENT 



A. 1.1.2-5 



C <~ -; 



r'.-COfcC lVl 



'1* 



Rockwell International 

Space Division 



ALPHA CDEGD 

10 20 



< 




MACH 



1.3 l.H 

NUMBER 



1.8 



CONFIGURATION 




BASELINE ORBITER VEHICLE REFERENCE OII^NSIONS 




COTTER CT GRAVITY XO - FS 1076.7 IN. WING AREA SW ■ 2690.00 


SQ.FT. 


OR YO • BL 0.0 IN. WINS SPAN BW - 78.055 


FT. 


M0f€NT REFERENCE 20 - WL 375.0 IN. M.A.C. CM • 39.560 


FT. 


BCOY LENGTH LB ■ 1290.3 


IN. 





MACH NIPPER 


0.900 


0.920 


0.950 


0.980 


1.050 


1.100 


1.200 


1.300 


1.500 


ALPHA IDEG) 


r 


G 


H 


I 


J 


K 


L 


M 


N 






AXIAL F 


ORCE COEFFI 


CIENT 








-10.000 


0.08810 


0.09640 


0.11200 


0.13450 


0.15270 


0.15790 


0. 16440 


0.16610 


0. 16460 


-5.000 


0.08770 


0.09450 


0.11040 


0.13600 


0.15260 


0.15760 


0. 16270 


0.16340 


0.16180 


-2.500 


0.08980 


0.09750 


0.11320 


. 1 3580 


0. 15350 


0.15790 


0.16200 


0. 16210 


0.15990 


0.0 


0.09070 


0.09900 


0.11450 


. 1 3460 


0.15410 


0.15B40 


0.16140 


0. 16110 


0.15770 


2.500 


0.08990 


0.09840 


0.11320 


0.13220 


0.15470 


0.15890 


0.16030 


0.15930 


0.15430 


5.000 


0.08760 


0.09590 


0.10990 


0.13070 


0. 154 30 


0.15880 


0.15890 


0.15600 


0. 14990 


7.500 


. 084 1 


0.09120 


0.10500 


0.12980 


0.15110 


0.15510 


0.15490 


0.15200 


0.14520 


10.000 


0.08170 


0.08930 


0.10280 


0.12960 


0.14590 


0.14900 


0.14940 


0.14720 


0.13980 


12.500 


0.08240 


0.08990 


0.10240 


0.12950 


0.14410 


0.145e0 


0.14530 


0.14270 


0.13540 


15.000 


0.08460 


0.09120 


0.10320 


0.12960 


0.14400 


0.14520 


0. 14440 


0. 14070 


0.13240 


17.500 


0.08710 


0.09400 


0.10470 


0.13030 


0.14450 


0.14560 


0.14390 


0.13940 


0.12950 


20.000 


0.08990 


0.09620 


0.10670 


0.13160 


0.14500 


0.14590 


0.14360 


0.13800 


0.12600 


22.500 


0.09270 


0.09890 


0.10900 


0.13340 


0.14510 


0.14610 


0.14310 


0.13610 


0.12250 


25.000 
30.000 


0.09570 


0.10180 


0.11150 


0.13510 


0.14510 


0.14620 


0.14250 


0.13390 


0. 11880 




















35.000 ' 
HO. 000 
45.000 • 

50.000 • 







































6 



FIGURE 4.1.1.2 -2 C~ " ' 
BASIC AXIAL FORCE COEFFICIENT 



4.1.1.2-6 



el vl -:;■■:• c. ; c im 



'1* 



Rockwell International 

Space Division 



< 



ALPHA CDEGD 
25 25 




3.5 

NUMBER 



6.0 











CONFIGURATION 










BASELINE 0R8ITER 


VEHICLE 




REFERENCE 


DIMENSIONS 






CENTER 


or GRAVITY 


XO 


- FS 


1076.7 


IN. 


WING AREA 


Sw « 


2690.00 


SO. 


FT. 




OR 


YO 


» BL 


0.0 


IN. 


WING SPAN 


Bw « 


78.056 


FT. 




MO-ENT 


REFERENCE 


20 


- U. 


375.0 


IN. 


M.A.C. 
BODY LENGTH 


CU « 
LB » 


39.560 
1290.3 


FT. 
(N. 







MACH NUTSER 


1 


1.100 


1.200 


1.300 


1.500 


2.000 


2.500 


3.000 


4.000 


5.000 




K 


L 


M 


N 


O 


P 


O 


R 


s 


!al=ha (DEG) 








AXIAL F 


ORCE CCEFFl 


CIENT 








i -io.ooo 


0.15790 


0. lfr+40 


0.16610 


0.16460 


0.14440 


0.13100 


0.12270 


0.11570 


0.11170 


1 -5.000 


0.15760 


0.16270 


0.16340 


0.16180 


0.14060 


0.12590 


0.11530 


0. 10660 


0. 10040 


-2.500 


0.15790 


0.16200 


0.15210 


0.15990 


0.13800 


0.12230 


. I 1 1 30 


0. 10090 


0.09290 


0.0 


0.15840 


0.16140 


0.16110 


0.15770 


0.13490 


0.11860 


0.10680 


0.09430 


0.08760 


2.500 


0. 15e90 


0.16030 


0.15930 


0.15430 


0.13120 


0.11490 


0.10300 


0.08880 


0.08190 


5.000 


0.15880 


0.15390 


0.15600 


0.14990 


0.12730 


0.11110 


0.09910 


0.08490 


C . 07590 


7.500 


0.15510 


0.15490 


0.15200 


0.14520 


0.12290 


0.10720 


0.09540 


0.08180 


. 07300 


10.000 


0.14900 


0.14940 


0.14720 


0.13980 


0.11830 


0.10300 


0.09210 


0.07910 


0.07060 


12.500 


0.14580 


0.14530 


0.14270 


0.13540 


0.11380 


0.09900 


0.08890 


0.07710 


0.06860 


15.000 


0. 14520 


0. 14440 


0.14070 


0.13240 


0.10940 


0.09490 


. 08600 


0.07530 


0.06770 


17.500 


0.14550 


0.14390 


. 1 3940 


0.12950 


0.10570 


0.09140 


0.08330 


0.07380 


0.06720 


20.000 


0.14590 


0. 14360 


0.13800 


0.12600 


0.10190 


0.08820 


. 08060 


0.07260 


0.066SO 


22.500 


0.14610 


0. 14310 


0.13610 


0.12250 


0.09800 


. 08500 


0.07830 


0.07150 


. 06650 


25.000 
30.000 < 
35.000 < 


0.14620 


0.14250 


0.13390 


0.11880 


0.09430 
0.08540 


0.08150 
0.07520 


. 07600 
0.07190 
0.06880 


. 07030 
0.06790 
. 06730 


0.06620 
. 06600 
0.06590 










HO. 000 














. 06700 


0.06550 


0. oe-50 


45.000 
50.000 














0.05h10 


0.08350 


0.06270 
0.05130 



ENGINEER ±&P_ 
DATE_i.OT.Arn5- 



FIGURE 4.1.1.2 -3 ^~~ '" 
BASIC AXIAL FORCE COEFFICIENT 



A. 1.1.2-7 



SL 7 



i~>. r* rz r* 

LLC ^ 



JM 



'Jt 



Rockwell International 

Space Division 



-20 



< 
CJ 



ALPHA CDEGD 

20 HO 

I I i 




" It 16 

NUMBER 



CONFIGURATION 




BASELINE CRBITER VEHICLE REFERENCE D1^E^5IC^S 




CENTER OF GRAVITY XO « FS 1076.7 IN. WING AREA SM ■ 2690.00 


SO. FT. 


OR YO - BL 0.0 IN. WING SPAN BW «= 78.056 


FT. 


MOftNT REFERENCE ZO - M_ 375.0 IN. M.A.C. CW - 39.560 


FT. 


BCOY LENGTH LB - 1290.3 


IN. 



T 





KACH MJ-6ER 


2.000 


2.500 


3.000 


4.000 


5.000 


8.000 


1 . 000 


15.000 


20.000 


ALPHA (C€G) 





P 


Q 


R 


S 


T 


U 


V 


w 








AXIAL F 


CRCE COEFFI 


CIENT 








-10.000 


0. 14440 


0.13100 


0.12270 


0.11570 


0.11170 


0.10670 


. 1 0670 


0.10670 


0.10670 


-5.000 


0.IH060 


0.12590 


0.11580 


0.10680 


0.10040 


0.09380 


. 09380 


0.09380 


0.09380 


-2.500 


0.13800 


0.12230 


0.11130 


0.10090 


0.09390 


. 08670 


0.08670 


0.08570 


0.08670 


0.0 


0.13490 


0.11860 


0.10680 


0.09430 


0.08760 


0.08000 


. 08000 


0.08000 


0.08000 


2.500 


0.13120 


0.11H90 


. 1 0300 


0.08880 


0.08190 


0.07440 


0.07440 


0.07440 


0.07440 


5.000 


0.12730 


0.11110 


0.09910 


0.08490 


0.07690 


0.06960 


0.05960 


0.06950 


0.06950 


7.500 


0.12290 


0.10720 


0.09540 


0.08180 


0.07300 


. 06560 


0.06560 


. 0.06560 


0.06560 


10.000 


0.11830 


0.10300 


0.09210 


0.07910 


0.07060 


0.06250 


0.06200 


0.06200 


0.06200 


12.500 


. 1 1 380 


0.09900 


0.08890 


0.07710 


0.06860 


0.06060 


0.06000 


. 06000 


. 06000 


15.000 


0.10940 


0.09490 


0.09600 


0.07530 


0.06770 


0.05970 


0. 05900 


0.05900 


. 05900 


17.500 


0.10570 


0.09IH0 


0.08330 


0.07380 


0.06720 


0.05950 


0.05860 


0.05860 


0.05850 


20.000 


0.10190 


0.08820 


0.08060 


0.07260 


0.06580 


0.05950 


0.05850 


0.05850 


0.05850 


22.500 


0.09800 


0.08500 


0.07830 


0.07150 


0.06650 


0.06010 


0.05900 


0.05900 


. 05900 


25.000 


0.09430 


0.08160 


0.07600 


0.07030 


0.06620 


. 06090 


. 06000 


0.06000 


0.06000 


30.000 


0.08540 


0.07520 


0.07190 
0.06880 
. 06700 
0.06410 


0.06790 
0.06730 
0.06560 
0.06350 


0.06600 
0.06590 
0.06450 
0.06270 
_0. 06135 


0.06250 
0.06260 
0.06180 
0.06150 
0.06130 


0.06170 
0.06160 
0.06080 
0.06100 
0.06130 


0.06170 
0.06160 
. 06080 
0.06100 
0.05130 


0.06170 
0.06160 
. 06080 
0.06100 
0.06130 


35.000 ' 
HO. 000 

H5.000 
50.00D ■ 










FIGURE 4.1.1.2 -U — ■ 
BASIC AXIAL FORCE COEFFICIENT 



4.1.1.2-8 



L?r:-n-i-ccec im 



€* 



Rockwell International 
Space Division 



ALPHA CDEG) 

20 30 40 50 

Ml! 



.15 



< 




CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE CONSIGNS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW >= 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MOI-ENT REFERENCE ZO = ML 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB » 1290.3 IN. 





VBAR 


0.005 


0.010 


0.020 


0.040 


0.060 


0.080 


ALPHA (OEG) 


A 


8 


C 


D 


E 


F 




VISCC 


KJS AXIAL F0 


RCE COEFFIC 


IENT 




20.000 


0.05850 


0.06500 


0.07800 


0.10400 


0.13000 


0.15600 


25.000 


0.06000 


. 06690 


0.08080 


0.10850 


0.13630 


0-16400 


30.000 


0.06170 


0.06930 


. 08440 


0.11460 


0. 14480 


0.17500 


35.000 


0.06160 


0.06930 


0.08H40 


0.11460 


0. 14480 


0.17500 


40.000 


0.06080 


0.06840 


0.08360 


0.11410 


0. 14450 


0.17500 


45.000 


0.06100 


. 06780 


0.08130 


0.10840 


0. 13540 


0.16250 


50 . 000 


0.06130 


. 06690 


0.07830 


0. 10100 


0.12360 


0.14700 



ENGINEER NASA 
DATE ~_"~ " 



FIGURE 4.1 
BASIC AXIAL 



1.2-5 

FORCE COEFFICIENT 



4.1.1.2-9 



L 



ccec jm 



'1* 



Rockwell International 

Spac* Division 



2.0 



ALPHA- CDEG] 

20 HO 

I"'' 



1.5 



< 



1.0 



0.5 




350000 400000 450000 500000 . 550000 600000 

ALTITUDE CFT.3 



650000 



700000 



750000. 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO = FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MGtCNT REFERENCE 20 - UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH L9 ' 1290.3 IN. 



ALPHA <DEG> 



20.000 
25.000 
30.000 
35.000 
40.000 
45.000 
50.000 



ALTITUDE (FT.) 



300000.0 
A 



350000.0 
B 



400000.0 

c 



450000.0 
D 



500000.0 

E 



550000.0 

F 



600000 . 
G 



HIGH ALTITUDE AXIAL FORCE 



0.15600 
0.16400 
0.17500 
0.17500 
0.17500 
0.16250 
0.14700 



0.52910 
0.58230 
0.62780 
0.65570 
0.67170 
0.66380 
0.63930 



0.91900 
1.01830 
1.09990 
1 . 15690 
1.18950 
1.18640 
1.15250 



1 . 12600 
1.25150 
1.35230 
1.42490 
1.46650 
1 .46600 
1.42700 



1.20470 
1 . 33980 
1 .44780 
1.52630 
1.57120 
1.57170 
1 .53080 



1.22960 
1.36770 
1.47810 
1.55840 
1 .60440 
1 .60520 
1.56370 



1 .23350 
1.37200 
I .48270 
1.56340 
1.60950 
1.61040 
1.56880 



ENGINEER JL&SA.. 
DATE 



FIGURE 4.1.1.2-6 
BASIC AXIAL FORCE COEFFICIENT 



\-/ 



4.1.1.2-10 



H-OCGO I IV 



* 



Rockwell Intematlonul 
Spac*DMiUon 



MACH NUMBER 



(Ul. (J I 

£5 

r r "i rj - ) i i ~r [ ttiti 

i rnrrr i 'i i rrr'rrTHT 




5 

ALPHA CDEG) 



CONFIGURATION 


BASELINE ORB ITER VEHICLE 


REFERENCE 01 MENS IONS 


CEMTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


or yo = a. 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOMENT REFERENCE ZO » UL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25. COO 


ce_E >de:-- 


A 


B 


c 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREME 


NT 






-*c.gco 


■3.;t7s 


. 07697 


0.07950 


0.08361 


. 08835 


0.08598 


0.08381 


0.06947 


-35. COO 


O.Oc-50 


0.06320 


. 05700 


0.07258 


0.07751 


0.08083 


0.06949 


. 07335 


-33 . 000 


0.05125 


0.05009 


0.05400 


0.06127 


0.06610 


0.07541 


0.05696 


0.Q7373 


-25.000 


0. 03^-25 


0.03539 


0.04100 


. 04936 


0.05567 


0.06625 


0.05295 


. C5333 


-20.-00 


0.01710 


. 1 997 


. 02900 


. 03575 


. 04536 


0.05495 


0.02752 


. 03975 


-15.000 


0.0C'-6i 


0.303:5 


. 1 700 


0.02164 


. 02724 


0.02959 


0.00911 


0.C2563 


-!C.:co 


-c.oc ;S7 


0.00 090 


0.00700 


. 00629 


0.01057 


0.01395 


-0 . 00056 


0.005C7 


-5.030 


v • ■* . V — — 


-0.00057 


0.00200 


0.00157 


. 00323 


0.00798 


-0 . 00555 


C 003=3 


- n 


0.3 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


C -'"l 


0.33731 


0.0OH12 


0.00400 


0.00130 


-0 . 002H8 


-0.00346 


. 0CB23 


0.00^9; 


10.300 


0.0l<-23 


0.01448 


0.01200 


0.00688 


0.00350 


0.00164 


0.01942 


0.01917 


15.330 


0.32952 


. 02839 


. 02300 


0.01787 


0.01527 


0.01576 


0.03446 


0.03SH4 


20.300 


. 05095 


C 04324 


. 04200 


0.03757 


0.04031 


. 04069 


. 05373 


. 05768 



:ng : seer 



&£: 



FIGURE 



4.1.1.2-' 

EFFECT OF 



ELEVCN 



4.1.1.2-11 



c r. - <-- 



•CCGC 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



0.400 



DELE CDEG) 

-50 -25 25 

I I I l | I I I I | I I I I 



UJ 

< 

8 




5 10 

ALPHA CDEG) 



15 20 



30 



CC*FIGURATI0N 



BASELINE 0RBITER VEHICLE 

CENTER Cf GRAVITY XO » FS 1076.7 IN. 

OR YO =• BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE OIMINSIONS 
WING AREA SW =■ 2690.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



DELE CDEG) 



-40.000 

-35.000 

-30.000 

-25.000 

-20 . 000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (PEG) 



ENGINEER J2CO- 
OATE_dkiUj£_ 



-10.000 
A 



-5.000 
S 



0.0 
C 



5.000 
D 



0.000 

E 



15.000 

F 



20.000 
G 



ELEVON AXIAL FORCE INCREMENT 



0.07752 
. 06H60 
0.05126 
0.03H26 
0.01710 
0.00H51 
-0.00197 
-0.00033 
0.0 
0.00731 

o.oiHsa 

0.02962 
0.05095 



0.07697 
0.06320 
0.05009 
0.03589 
0.01997 
0.00816 
0.00080 
-0 . 00057 
0.0 

0.0OH12 
0.01448 
0.02839 
0.04824 



0.07960 

0.06700 

0.05400 

0.04100 

0.02800 

0.01700 

0.00700 

0.00200 

0.0 

0.00400 

0.01200 

0.02300 

. 04200 



0.08361 

0.07258 

0.06127 

0.04936 

0.03575 

0.02154 

0.00829 

0.00157 

0.0 

0.00130 

0.00688 

0.01787 

0.03757 



FIGURE 4.1.1.2-8 

EFFECT OF ELEVON 



o. 

0. 
0. 
0. 
0. 
0. 
0. 
0. 
0. 
-0. 
0. 
0. 
0. 



08835 

07751 

06610 

05567 

04536 

02724 

01057 

00323 



00248 

00350 

01527 

04031 



0.08598 
0.08083 
0.07541 
0.06625 
0.05495 
0.02959 
0.01395 
0.00798 
0.0 
-0.00346 
0.00164 
0.01576 
. 04069 



0.08331 
. 06949 
0.05696 
0.05295 
0.02752 
0.00911 
-0.00066 
-0.00555 
0.0 

0.00823 
0.01942 
0.03446 
0.05373 



25.000 
H 



0.C8947 

0.07835 

0.07373 

0.05393 

0.03976 

0.02568 

. 00507 

0.00393 

0.0 

0.00791 

0.01917 

. 03844 

0-05758 



4.1.1.2-12 



D 



7 Z - ^ '■ 



ccec im 



a 



Rockwell International 

Space Division 




5 10 

ALPHA CDEG) 



25 



CONFIGURATION 




basel:!*: obiter vehicle 


REFERENCE DII^NSIONS 




CENTER OF GRAVITY X0 « FS 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR Y0 - SL 0.0 IN. 


WING SPAN BW «■ 78.055 


FT. 


ICftNT REFERENCE 20 » U. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 











ALPHA 


(OEG) 










-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 




A 


5 


c 





E 


F 


G 


H 


D€_£ .0E0-: 






ELEV 


ON AXIAL FO 


RCE INCREKEJ 


MT 






— 'C.CJC 


. 02355 


0.10724 


0.0S56C 


0.09127 


0.09808 


0.07674. 


0.05061 


0.00333 


-35.00C 


0.07153 


0.09556 


. 07800 


0.079H9 


0.08563 


0.06680 


0.04565 


0.00072 


-30.000 


.0.05075 


0.06451 


0.06100 


0.06593 


0.07161 


0.05618 


0.03907 


-0.003=9 


-25. COO 


C. 03169 


0.04899 


0.04800 


0.05343 


0.05704 


0.04633 


0.03215 


-0.00865 


-20.000 


0.015-tO 


0.03475 


0.03800 


0.04140 


0.04468 


0.03687 


0.02274 


-0.01443 


-15.0C0 


-0.00023 


0.01992 


. 02200 


0.02732 


0.03095 


0.02162 


0.00734 


-0.01 125 


-10.000 


-0 . 00727 


0.00735 


0.01000 


0.01266 


0.01417 


0.00909 


0.00108 


0.00104 


-5.000 


-0.00584 


0.00160 


0. 00250 


0.00321 


0.00422 


0.00204 


0.00122 


0.00094 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00673 


0.00430 


0.00400 


0.00285 


. 00303 


0.00551 


0.00459 


0.00558 


10. co: 


C. 01906 


0.01387 


0.01300 


0.01160 


0.01057 


0.01620 


0.00960 


0.02161 


is. coo 


0.03185 


0.02925 


0.02500 


0.02534 


0.02345 


0.02730 


0.02931 


. 06065 


20.000 


0.7-632 


0.0450! 


0.04300 


. 04070 


0.04541 


0.05574 


. 05279 


0.09489 



:-j:-:-£E.3 



s&fc 



FIGURE 4.1.1.2-9 
EFFECT OF ELEVON 



4.1.1.2-13 



sc72-or-i-ccec ir 



€> 



Rockwell International 

Spac* Division 



MACH 



.15 



.10 



lu 

< 



.05 



NUMBER 

I II I 



-.05 

-ao 



TTT 



0.800 

I l I l 



-50 



DELE 

-25 



CDEG3 
o 



25 



Tl I I 



I I I I 




I I I I I I -I I I 1 I I ! I I I I I I I I 
-15 -10-5 5 



I I I I 



I I I 



I I ij 



I I I..I I I I 



Mil 



I II i 



JH. 1. 1 I I 



II I I 



I i I I 



J_L 



10 



15 



20 



25 



ALPHA CDEGD 



CONFIGURATION 




BASELINE ORSITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW =» 39.560 


FT. 




BODY LENGTH L8 - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREME 


NT 




-HO. 000 


0.10920 


0.11966 


0.10850 


0.11017 


0.08464 


0.06655 


. 04054 


0.02615 


-35.000 


0.08417 


0.09951 


0.09150 


0.09191 


0.07138 


0.05320 


0.03454 


0.02681 


-30.000 


0.06078 


0.07933 


. 07300 


0.07221 


0.05864 


0.04313 


0.02891 


0.02663 


-25.000 


0.03949 


0.06063 


0.05850 


0.05638 


0.04778 


0.0336O 


0.02328 


0.02517 


-20.000 


0.02195 


0.04290 


0.04300 


0.04319 


0.03559 


0.02601 


0.01649 


0.02161 


-15.000 


0.01016 


0.02740 


0.02800 


0.02992 


0.02393 


0.01678 


0.01197 


0.01463 


-10.000 


0.00040 


0.01420 


0.01500 


0.01525 


0.01290 


0.00957 


0.00536 


. 00506 


-5.000 


-0.0041B 


... 0.00289 


0.00350 


0.00382 


0.00239 


0.00075 


-0.00301 


-0.00374 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00872 


0.00330 


0.00300 


0.00333 


0.00343 


0.00762 


0.00339 


0.00827 


10.000 


0.02105 


0.01170 


0.01300 


0.01245 


0.01416 


0.01942 


0.01717 


0.02810 


15.000 


0.03774 


0.02610 


0.02850 


0.02948 


0.03004 


0.03919 


0.04135 


0.C6421 


20.000 


0.06171 


0.04^*95 


. 05000 


0.05244 


0.05322 


0.06245 


0.06642 


0.10421 



ENGINEER DCO 



FIGURE 4.1.1.2-10 

EFFECT. OF ELEVON 



30 



4.1.1.2-14 



cr'7 r 



/ *r - 






-cceo jm 



WjFl Rockwell International 

Space Division 



MACH NUMBER 



0.900 



UJ 

< 
o 
o 




,05' ! I 1 I I I I I I 

-20 -15 -10 



5 10 

ALPHA CDEGD 









CONF 


GURA 


BASELINE ORBITER 


VEHICLE 




CENTER OF GRAVITY 


XO 


' FS 


1076.7 


IN. 


OR 


YO 


» BL 


0.0 


IN. 


MCfENT REFERENCE 


20 


- WL 


375.0 


IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BUI = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BODY LENGTH LB » 1290.3 IN. 



T 











. ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREKE 


MT 






-40 . 000 


0.11562 


0.13437 


0.12500 


0.11356 


0.07616 


0.05639 


0.03051 


0.020S3 


-35.000 


0.09135 


0.11335 


. 1 0600 


0.09152 


0.06615 


. 04967 


0.03058 


0.02310 


-30 . 000 


0.06823 


0.09367 


0.08700 


0.07195 


0.05483 


0.04296 


0.02907 


0.02391 


-25.000 


0.04728 


0.07305 


. 06950 


0.05616 


0.04533 


0.03555 


0.02748 


. 02303 


-20 . 000 


0.0277H 


0.05509 


. 05200 


0.04084 


0.03547 


0.03006 


0.02499 


0.02016 


-15.000 


0.00979 


. 03442 


0.03500 


0.02817 


0.02536 


0.02209 


0.02100 


0.01550 


-10.000 


0.00007 


0.01899 


0.01900 


0.01588 


0.01403 


0.01231 


0.01335 


. 00809 


-5.0OO 


-0.00244 


0.00502 


0.00700 


0.00512 


0.00645 


0.00356 


0.00244 


0.00058 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5. COO 


0.00639 


0.00329 


0.00100 


0.00136 


0.00187 


. 00769 


0.00856 


0.00890 


10.000 


0.019m 


0.01229 


0.00970 


0.01103 


0.01283 


0.02091 


0.01790 


0.03160 


15.000 


0.03677 


0.02748 


. 02800 


0.02695 


0.03115 


0.03822 


0.04086 


. 074H4 


20 . 000 


. 05633 


0.04956 


0.05300 


0.05349 


0.05473 


0.06304 


0.07252 


0.11885 



ENGI 
DATE 



NEER DCO 



FIGURE 



4.1.1.2- 

EFFECT OF 



11 

ELEVQN 



4.1.1.2-15 



(■ ■ ■• r- -■ 

» i_ I .... 



.--G'. C JM 



€> 



Rockwell International 

Space Division 



MACH NUMBER 
l5 < I "i ")" J 'T V l"l I 



< 

Q 



0.950 

I I I I i I I l TTT 



DELE CDEGD 

-50 -35 25 

I I I I I I i ! I I I M II 




I I I I 



. 05 l I I I I I I I I I I I I I I I I I I I I I 1 I 
-20 -15 -10 -5 



I I I I I I I I | I I I I 



I I I I 



I I I ! I I I I I I I I I I 1 I I I I I 1 I [ 
5 10 15 20 25 30 



ALPHA CDEG3 



COFIGURATION 


BASELINE ORBITER \£HICL£ 


REFERENCE DIltNSICNS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOENT REFERENCE ZO - M. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB » 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


8 


c 


D 


E 


F 


G 


H 






ELEV0N AXIAL. FO 


RCE INCRETE 


NT 






-40.000 


0.11633 


0.13052 


0.12350 


0.10315 


0.08155 


0.05717 


0.01180 


-0.01357 


-35.000 


0.09661 


0.11052 


0.10600 


0.08945 


0.07029 


0.05111 


0.01824 


-0.00787 


-30.000 


0.07533 


0.09209 


0.08800 


0.07530 


0.05908 


0.04440 


. 02399 


-0.00252 


-25.000 


0.05355 


0.07320 


.0.07100 


0.06005 


0.05193 


0.03788 


0.02804 


0.00297 


-20.000 


0.03290 


0.05459 


0.05400 


0.04545 


0.04174 


0.02984 


0.03059 


0.00874 


-15.000 


0.01480 


0.03569 


0.03500 


0.03000 


0.02859 


0.01774 


0.02643 


0.01179 


-10.000 


0.00188 


0.01751 


0.01800 


0.01510 


0.01450 


0.00612 


0.01145 


0.00933 


-5.000 


-0.00314 


0.00353 


0.00550 


0.00567 


0.00251 


0.00026 


0.00215 


0.00110 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00822 


0.00453 


0.00400 


0.00289 


0.00308 


0.00622 


0.00381 


0.00537 


10.000 


0.02089 


0.01153 


0.01200 


0.01309 


0.01202 


0.01849 


0.02173 


0.03169 


15.000 


0.03433 


0.02531 


0.02950 


. 03020 


0.02883 


0.03614 


0.04394 


0.07749 


20.000 


0.05114 


0.04595 


0.05500 


0.05710 


0.05270 


. 05978 


0.08041 


0.12804 



ENGIt-£ER T YTft 
PATERA =Jr-r3g— 



FIGURE 4.1.1.2-12 

EFFECT OF ELEVCIN 



2*. 1.1.2-16 



D72-SH-CCCC IM 



'1* 



Rockwell International 

Spaca Division 



MACH NUMBER 
l5 i i I ll ll I I 



0.980 



DELE CDEG) 

50 -25 



< 

a 




5 10 

ALPHA CDEG) 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE Oir-CNSICNS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO - SL 0.0 IN. 


WING SPAN BW * 78.056 


FT. 


MOfENT REFERENCE 20 = W. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BOGY LENGTH LB - 1290.3 


IN. 



T 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


B 


C 





E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCRE^S 


NT 






-HO . 000 


0.11608 


0.12903 


0.12514 


0.10324 


0.086S8 


. 05967 


0.01881 


-0.01295 


-35.000 


0.09890 


0.11013 


. 1 0748 


0.09045 


0.07558 


0.05332 


0.C2264 


-0 . 00685 


-30 . 000 


0.07908 


0.09189 


0.08950 


. 07702 


0.06450 


0.04586 


0.02581 


-0.00154 


-25.000 


0.05732 


. 07267 


. 07223 


0.06221 


0.05587 


0.03858 


0.02836 


0.OC429 


-20 . 000 


0.03522 


0.05245 


. 05509 


0.04733 


0.04437 


0.02969 


0.02795 


0.00990 


-15.000 


0.01571 


0.03312 


0.03615 


0.03135 


0.02999 


0.01652 


0.02289 


0.01111 


-10.000 


. 002H3 


0.01559 


0.01882 


0.01602 


0.01493 


0.00502 


0.00965 


0.00919 


-5.000 


-0.00315 


0.00294 


0.00536 


0.00592 


0.00357 


-0 . 00062 


0.00154 


0.00159 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.009m 


0.00605 


0.00511 


0.00437 


0.00478 


0.00684 


0.00308 


0.00449 


10.000 


0.02132 


0.01346 


0.01337 


0.01475 


0.01433 


0.01879 


0.02340 


0.03142 


15.000 


0.03231 


0.02789 


0.03170 


0.03281 


0.03282 


0.03810 


0.04837 


0.07849 


20 . 000 


0.04490 


. 04498 


. 05948 


. 05923 


0.05842 


0.06510 


0.08572 


0.13301 



ENGINEER DCQ 



FIGURE 



4.1. 1.2- 

EFFECT OF 



13 
ELEVGN 



4.1.1.2-17 



£D75-j;!:-CCCC 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.050 



DELE C0EG3 

50 -25 



UJ 

< 

a 




-20 



-15 



-to 



-5 



5 10 

ALPHA CDEGD 



30 



configuration 


BASELINE 0R9ITER VEHICLE 


REFERENCE DI^NSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


UING AREA SW = 2690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MOt-ENT REFERENCE ZO » U. 375.0 IN. 


H.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FC 


RCE INCRErE 


^T 






-HO. 000 


0.11175 


0.12779 


0.13150 


0.10838 


0.10139 


0.06886 


. 03978 


0.00985 


-35.000 


0.10092 


0.11241 


0.11250 


0.09417 


0.08957 


. 06037 


0.03627 


0.01003 


-30 . 000 


0.08551 


0.09277 


0.0S400 


0.07886 


. 07568 


0.04992 


0.03104 


0.00S95 


-25.000 


. 06576 


0.07134 


0.07550 


0.06492 


0.06177 


0.03966 


0.02619 


0.00880 


-20.000 


. 03902 


. 0464 1 


0.05700 


. 04930 


. 04660 


0.02939 


. 02007 


0.00829 


-15.000 


0.01686 


0.02528 


0.04000 


0.03425 


0.03169 


0.01688 


0.01258 


0.00791 


-10.000 


0.00287 


0.00984 


. 02200 


0.02003 


0.01655 


0.00701 


0.00492 


. 00634 


-5.000 


-0.00240 


0.00309 


. 00630 


. 00567 


0.00598 


-0 . 00058 


. 00033 


0.00288 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01079 


0.00722 


0.00500 


. 00872 


0.00951 


0.00952 


0.00458 


0.00401 


10.000 


0.02176 


0.01852 


0.01650 


0.01968 


0.02093 


0.02015 


0.02540 


0.03048 


15.000 


0.02712 


0.03287 


0.03800 


0.03978 


. 04597 


0.04483 


0.05859 


0.07952 


20.000 


0.02853 


0.04733 


0.07300 


0.06393 


0.07784 


0.08325 


0.09884 


0. I44| 1 



£!MG!NEERJ2C0 
DATEYJL-iL-3i~ 



FIGURE 4.1.1.2-14 

EFFECT OF ELEVON 



4.1.1.2-18 



C 5 



t o c e C ! M 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



1. 100 



DELE CDEG) 

-50-25 25 

Mil 



LU 

< 



T 




5 10 

ALPHA CDEGD 



CONFIGURATION 




BASELlt^ ORBITER VEHICLE 


REFERENCE DIfENSIONS 




CENTER OF GRAVITY XO » F5 1076.7 IN. 


WING AREA SU = 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW - 78.055 


FT. 


MOMENT REFERENCE ZO » WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB » 1390.3 


IN. 











ALPHA 


(DEG) 








-10.000. 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCRErE 


NT 






-HO. 000 


0.10382 


0.13586 


0.12100 


0.09837 


0.09803 


0.06940 


0.03985 


0.01211 


-35.000 


0.09732 


0.11869 


0.10400 


0.08274 


0.08523 


0.05965 


0.03426 


0.00867 


-30 . 000 


0.08503 


0.09992 


. 08530 


0.06770 


0.07275 


0.04809 


0.02772 


0.00614 


-25.000 


0.06760 


0.07989 


0.06900 


0.05372 


0.05004 


0.03808 


0.02213 


0.00509 


-20 . 000 


0.04180 


0.05981 


0.05200 


0.03936 


0.04675 


0.02749 


0.01529 


0.00419 


-15.000 


0.02031 


0.03920 


0.03H50 


0.02701 


0.03271 


0.01809 


0.00846 


0.00281 


-10.000 


0.00399 


0.0230H 


0.01900 


0.01520 


0.01858 


0.00981 


0.00142 


0.00118 


-5.000 


-0.00200 


0.01015 


. 00750 


0.00497 


0.00671 


0.00083 


-0.00172 


-0.00047 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.005H6 


0.00172 


0.00550 


0.00798 


0.01055 


0.00798 


0.00630 


0.00630 


10.000 


0.0IH12 


0.01723 


0.01700 


0.01782 


0.02151 


0.02014 


0.02286 


0.03099 


15.000 


0.02123 


0.03742 


0.03750 


0.04031 


0.04076 


0.04457 


0.05384 


0.07550 


20.000 


0.02668 


0.05927 


0.06800 


0.07086 


0,07002 


. 08022 


0.09251. 


0.14124 



ENGINEER PCO 



FIGURE 



4.1.1.2- 
EFFECT OF 



15 

ELEVON 



4.1.1.2-19 



* 



Rockwell International 

Spaca Division 



MACH NUMBER 
l5 ' lilt 



DELE CDEGD 

-50 -25 

[" I I I I | I I I l 



UJ 

< 

Q 




ALPHA CDEG3 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE ZO » UL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




9COY LENGTH LB - 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREME 


^^■ 






-HO. 000 


0.06780 


0.09795 


0.10150 


0.09523 


0.08358 


0.06401 


0.03929 


0.01441 


-35.000 


0.08026 


0.08680 


0.08900 


0.07984 


0.06977 


0.05313 


0.03235 


0.01227 


-30.000 


0.07165 


0.07581 


0.07700 


0.06527 


0.05576 


0.04209 


0.02593 


0.01129 


-25.000 


0.05986 


0.06011 


0.06000 


0.05070 


0.04336 


0.03079 


0.01944 


0.01035 


-20.000 


0.04466 


0.04511 


0.04400 


0.03570 


0.03126 


0.02019 


0.01294 


0.00902 


-15.000 


0.02713 


0.02781 


0.02800 


0.02325 


0.01927 


0.01005 


0.00501 


0.00601 


-10.000 


0.00957 


0.01259 


0.01500 


0.01226 


0.00989 


0.00080 


0.00148 


0.00091 


-5.000 


-0.00057 


0.00306 


0.00550 


0.00458 


0.00243 


-0.00169 


-0.00255 


-0 . 00282 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00553 


. 00002 


0.00300 


-0.00418 


0.00702 


0.00831 


0.00844 


0.00998 


10.000 


0.01429 


0.00772 


0.0t350 


0.01575 


0.01560 


0.01856 


0.01952 


0.02803 


15.000 


0.02414 


0.01800 


0.02800 


0.03550 


0.03113 


0.03659 


0.05156 


. 06534 


20 . 000 


0.03445 


0.04115 


. 04450 


. 0.04963 


0.05136 


0.06132 


0.09239 


0.10981 



ENGINEER OCp 
DATE.XA.^Sr^E 



FIGURE 



4.1.1.2- 

EFFECT OF 



16 
ELEVGN 



4.1.1.2-20 



SC72-2H-OC6C IM 



e 



Rockwell International 

Space Division 



MACH NUMBER 



1.300 



-50 



DELE CDEG) 
-25 o 



< 

CJ 

a 



-.05 




5 10 

ALPHA CDEGD 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DIhCNSIONS 




CENTER CF GRAVITY XO » FS 107S.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


Cfi YO » BL 0.0 IN. 


WING SPAN BW « 78.056 


FT. 


MCtCNT REFERENCE ZO = W_ 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 













ALPHA 


(DEG) 












-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 




DELE (DEG) 


A 


8 


c 


D 


E 


F 


G 


H 










ELEV 


CN AXIAL FO 


RCE INCRE^E 


NT 






I 


-40 . 000 


0.07811 


0.11546 


0.09000 


0.08774 


0.07846 


0.06046 


0.03666 


0.01587 




-35.000 


0.06799 


0.09698 


0.07650 


. 07627 


0.06416 


0.05165 


0.03199 


0.01454 






-30.000 


0.05955 


0.07827 


0.06400 


0.06456 


0.05049 


0.03948 


0.02734 


0.01436 






-25.000 


0.05050 


0.06148 


0.05100 


0.05131 


0.03827 


0.03147 


0.02237 


0.01337 






-20 . 000 


0.04072 


0.04495 


0.03750 


0.03701 


0.02573 


0.02121 


0.01584 


0.01199 






-15.000 


0.02707 


0.03045 


0.02750 


0.02529 


0.01794 


0.01303 


0.01110 


0.00894 






-10.000 


0.00924 


0.01767 


0.01650 


0.01301 


0.00926 


0.00378 


0.00481 


0.00420 






-5.000 


-0.00069 


0.00665 


0.00450 


0.00331 


0.00069 


-0.00302 


-0.00167 


-0 . 00294 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 






5.000 


0.00370 


0.00115 


0.00100 


0.00628 


0.00885 


0.0C452 


0.00566 


0.01095 






10.000 


0.00S92 


0.00914 


0.01100 


0.01451 


0.01679 


0.01389 


0.01567 


0.02419 






15.000 


0.01961 


0.01995 


0.02250 


0.02999 


0.03179 


0.03148 


. 03467 


0.04202 




ENGINE 


20.000 


. 030S9 


0.03437 


0.04100 


0.04775 


0.04939 


0.05026 


0.06301 


0.06525 




«_P.C.o . 




FIGURE 


4.1.1.2 


-17 












DAJEO.« 


.--1--78-- 






EFFECT 


F ELEVON 











4.1.1.2-21 



*> 



Rockwell International 
Spac* Division 



MACH NUMBER 



1.500 



DELE CDEGD 

-50 -25 25 

I I I I | I I I I | i I I I | 



< 

o 




_.05U_L-i 



5 10 

ALPHA CDEG) 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER Cf GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO - a. 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE IDEG) 


A 


B 


C 





E 


F 


G 


H 






ELEV 


ON AXIAL FOI 


RCE INCREME 


^iT 






-HO. 000 


0.13433 


0.09923 


0.08467 


0.06758 


0.05549 


0.04815 


0.04014 


0.03121 


-35.000 


0.10613 


0.07731 


0.06803 


0.05644 


0.04669 


0.03982 


0.03568 


0.02983 


-30.000 


0.08115 


0.05822 


0.05140 


0.04577 


0.03852 


0.03647 


0.03061 


0.02857 


-25.000 


0.05566 


0.04313 


0.03948 


0.03534 


0.03075 


0.02962 


0.02578 


0.02518 


-20.000 


0.03432 


0.03018 


0.02660 


0.02655 


0.02014 


0.02144 


. 02064 


0.01877 


-15.000 


0.02210 


0.01968 


0.01814 


0.01619 


0.01263 


0.01375 


0.01448 


0.01413 


-10.000 


0.01669 


0.01069 


0.01123 


0.00740 


0.00448 


0.00577 


0.00838 


0.00864 


-5.000 


0.00718 


0.00370 


0.00470 


0.00111 


-0.00017 


-0.00076 


0.00291 


0.00434 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00246 


-0.00108 


0.00249 


0.00549 


0.00544 


0.00645 


0.00586 


0.00118 


10.000 


-0.00164 


0.00513 


0.00913 


0.01415 


0.01264 


0.01576 


0.01308 


0.00498 


15.000 


0.00191 


0.01456 


0.02046 


0.02731 


0.02700 


0.02857 


0.02272 


0.01548 


20.000 


0.00693 


0.02538 


0.03274 


0.04179 


0.04467 


0.04386 


0.03830 


0.03092 



ENGINEER OCfi 



FIGURE 4.1.1.2-18 

EFFECT OF ELEVCN 



4.1.1.2-22 



SC72-SK-CCC0 1M 



€> 



Rockwell International 
Space Division 



MACH NUMBER 
15 rTT-TT 



DELE 

50 -25 



UJ 
< 

u 

Q 




CONFIGURATION 


BASELINE ORBITEP VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 3690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 7B.055 FT. 


MO>€NT REFERENCE ZO » WL 375.0 IN. 


M.A.C CW - 39.550 FT. 




BCCY LENGTH LB * 1290.3 IN. 





ALPHA (OEG) 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30 . 000 


DELE (OEG) 


A 


B 


c 


O 


E 


F 


G 


H 


I 








ELEVON AX 


IAL FORCE I 


NCREMENT 








-HO. 000 


0.06742 


0.06107 


0.05310 


. 03605 


0.02918 


0.02157 


0.01430 


0.01048 


. 00487 


-35.000 


0.05361 


0.04875 


0.04300 


0.02870 


0.02371 


0.01764 


0.01268 


0.00933 


0.00570 


-30.000 


. 0H068 


0.03659 


0.03300 


0.02153 


0.01673 


0.01363 


0.00926 


0.00641 


0.00553 


-25.000 


0.02925 


0.02542 


0.02400 


0.01667 


0.01221 


0.00892 


0.00447 


0.00417 


0.00486 


-20.000 


0.01719 


0.01550 


0.01500 


0.01208 


0.00770 


0.00311 


0.00062 


0.00070 


0.00132 


-15.000 


0.009S8 


0.01001 


0.01000 


0.00512 


0.00115 


-0.00200 


-0 . 00263 


-0.00243 


-0.00271 


-10.000 


0.00356 


0.00337 


0.00500 


0.00106 


-0.00244 


-0.00395 


-0 . 00494 


-0 . 00469 


-0.00415 


-5.000 


0.00025 


0.00090 


0.00100 


-0.00125 


-0.00359 


-0.00352 


-0.00384 


-0.00465 


-0.00349 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00123 


0.00133 


0.0 


. 00333 


0.00342 


0.00493 


0.00563 


. 00702 


0.00805 


10.000 


0.00480 


0.00476 


. 00600 


0.00955 


0.00910 


0.01231 


0.01442 


0.01539 


0.02153 


15.000 


0.00985 


0.01149 


0.01500 


0.01777 


0.02191 


0.02278 


0.02407 


0.03120 


0.03848 


20.000 


0.01374 


0.01875 


. 02300 


0.02971 


0.03610 


. 03949 


0.03790 


. 04837 


0.05652. 


INGINEER PCO 




FIG 


SURE 4. 


I . 1 . 2-19 













DATE..Zfi^ir28 



EFFECT OF ELEVON 



Z*. 1.1. 2-23 



SL ■/::-s:-i-occc IM 



* 



Rockwell International 
Space Division 



MACH NUMBER 



CDEGD 
o 



UJ 

< 




5 10 

ALPHA CDEGD 



COT 1 (JURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCttNT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 3690.00 SQ.FT. 
WING SPAN SW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB » 1390.3 IN. 











ALPHA 


<C€G) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE 1NCREME 


NT 






-MO. 000 


0.04594 


0.03652 


0.02500 


0.02143 


0.02027 


0.01557 


0.01124 


0.01133 


-35.000 


0.03632 


0.02889 


0.02000 


0.01675 


0.01546 


0.01263 


0.00855 


. 00750 


-30.000 


0.02663 


0.02205 


0.01550 


0.01265 


0.01030 


0.00934 


0.00591 


0.00457 


-35.000 


0.01931 


0.01677 


0.01150 


0.00954 


0.00695 


0.00630 


0.00420 


0.00165 


-20.000 


0.01241 


0.01158 


0.00800 


0.00604 


0.00411 


0.00300 


0.00181 


-0.00038 


-15.000 


0.00782 


0.00747 


0.00400 


0.00318 


0.00173 


0.00074 


0.00001 


-0.00279 


-10.000 


0.00349 


0.00362 


0.00300 


0.00148 


-0.00047 


-0.00133 


-0.00187 


-0.00563 


-5.000 


0.00143 


0.00177 


0.00100 


-0.00012 


-0 . 00006 


-0.00172 


-0.00119 


-0.C0532 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00011 


-0.00021 


0.00100 


0.00162 


0.00151 


0.00191 


0.00427 


0.00599 


10.000 


-0.00065 


0.00174 


0.00300 


0.00506 


0.00585 


0.00795 


0.00964 


0.01512 


15.000 


0.00106 


0.00517 


0.00600 


0.01081 


0.01339 


0.01823 


0.02066 


0.03132 


20.000 


0.00208 


0.00677 


0.01200 


0.01738 


0.02503 


. 03070 


0.03731 


0.04685 



ENGINEER £>CO 
DATE.7J>rjg:-2g 



FIGURE 4.1.1.2-20 
EFFECT OF ELEVON 



4.1.1.2-24 



SL72-SH-CC6C 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



3.000 



DELE 

-50 -25 

I I I I 



CDEG) 





Id 
< 

U 

a 



r 




25 30 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORB1TER VEHICLE 


REFERENCE DINENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW =■ 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MOMENT REFERENCE ZO ■ M. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BCOY LENGTH LB ' 1290.3 IN. 



DELE (OEG) 



-HO. 000 

-35 . 000 

-30 . 000 

-25.000 

-20 . 000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20 . 000 



15.000 

F 



20.000 
G 



ALPHA (OEG) 



25.000 
H 



30.000 
I 



35.000 
J 



40.000 
K 



0.01567 
0.01263 
. 00934 
0.00630 
0.00300 
. 00074 
-0.00133 
-0.00172 
0.0 

0.00191 
0.00795 
0.01823 
0.03070 









-0, 
-0, 
0. 
0. 
0. 
0. 
0. 



01124 

00856 

00591 

00420 

00181 

0000 1 

00187 

00119 



00427 

00964 

02066 

03731 



ENGINEER J?CO 
DATE^XQl-i-X* 



FIGURE 4. 



ELEVON AXIAL FORCE INCREfCNT 



45.000 

L 



0.01133 

0.00750 

0.00457 

0.00165 

-0.00038 

-0.00279 

-0.00563 

-0.00532 

0.0 

0.00599 
0.01512 
0.03132 
0.04685 



0.00731 

0.00702 

0.00535 

0.00402 

0.00175 

-0.00302 

-0.00605 

-0.00649 

0.0 

0.00682 
0.01884 
0.03423 
0.04740 



0.00391 

0.00238 

0.00116 

0.00006 

0.00030 

-0.00315 

-0 . 00554 

-0.00626 

0.0 

0.00926 
0.02299 
0.03835 
0.05224 



. 00323 

0.00149 

-0 . 00026 

-0.00146 

0.00040 

-0.00103 

-0.00379 

-0.00516 

0.0 

0.01186 
0.02732 
0.04289 
. 05774 



0.00788 
0.00524 
0.00371 
0.00241 
0.00284 
0.00097 
-0.00141 
-0 . 00332 
0.0 

0.01208 
. 03035 
0.04740 
. 06573 



1.2-21 



EFFECT OF ELEVGN 



4.1.1.2-25 



€> 



Rockwell International 

Space Division 



J_ 



MACH NUMBER 



.10 



LU 

< 




-.05LU-1 



-10 



5 10 

ALPHA CDEGD 



15 



20 



25 



COF IGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER CF GRAVITY XO » FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MGfENT REFERENCE ZO - 14. 375.0 IN. 



REFERENCE DII-ENSI0NS 
WING AREA SW - 2590.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW » 39.560 FT. 

90OY LENGTH LB - 1290.3 IN. 



DELE (DEG) 



-40.000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



-10.000 
A 



-5.000 
.8 



0.0 
C 



ALPHA (DEG) 



5.000 
D 



10.000 

E 



15.000 

F 



0.04019 

0.03103 

0.02223 

0.01571 

0.00938 

0.00577 

00269 

00096 



00176 
00242 
00301 



-0.00319 



0.03349 
0.02563 
0.01926 
0.01440 
0.01002 
0.00580 
0.00298 
0.00103 
0.0 
-0.00138 
-0.00077 
0.00174 
0.00376 



SLEVON AXIAL FORCE INCREMENT 



20.000 

G 



25.000 
H 



0.02840 

0.02270 

0.01600 

0.01200 

0.00800 

0.00450 

0.00200 

0.00050 

0.0 

0.0 

0.00200 

0.00500 

0.00400 



.02377 
.01687 
.01146 
.00844 
.00552 
.00392 
0.00122 
0.00061 
0.0 

0.00112 
0.00435 
0.00741 
0.01049 










-0 








.01741 

.01101 

.00709 

.00425 

.00255 

.00101 

.00014 

.00058 

.0 

.00136 

.00504 

.00938 

.01250 



ENGINEER £Qo 



FIGURE 4.1.1.2-22 
EFFECT OF ELEVON 



0.01216 

0.00675 

0.00278 

-0.00003 

-0.00177 

-0.00140 

-0.00172 

-0.00134 

0.0 

0.00217 
0.00640 
0.01072 
0.01775 



O.D0880 
0.00317 
-0.00056 
-0.00324 
-0.00401 
-0.00405 
-0.00376 
-0.00205 
0.0 

0.00273 
0.01004 
0.01771 
0.02984 



0.00651 

0.00246 

0.00017 

-0.00161 

-0.00339 

-0.00478 

-0.00590 

-0.00405 

0.0 

0.00375 
0.01249 
0.02546 
0.04353 



30 



4.1.1.2-26 



E 72-SH-OCec IM 



a 



Rockwell International 

Space Division 



MACH NUMBER 
• 15 i i ll I I M I 



4.000 



,10 



uj 

< 

Q 



.05 



.05 



I i i I I I I t 



J_L 



I I I I 



■J- I.. I i 



10 



15 







30 

CDEGD 



CON 7 1 (JURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MOTENT REFERENCE ZO - M. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.055 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB - 1890.3 IN. 





ALPHA (OEG) 




15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELE (OEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVON AX 


IAL FORCE ! 


NCREMENT 






-HO. 000 


0.01216 


. 00880 


0.00651 


0.00599 


0.00325 


0.00313 


0.00764 


-35.000 


0.00675 


0.00317 


0.00246 


0.00539 


0.00222 


0.00189 


. 00630 


-30.000 


0.00278 


-0.00056 


0.00017 


0.00395 


0.00046 


-0.00031 


0.00349 


-25.000 


-0.00003 


-0 . 00324 


-0.00161 


0.00238 


-0.00134 


-0.00239 


0.00117 


-20 . 000 


-0.00177 


-0.00401 


-0 . 00339 


0.00037 


-0.00265 


-0.00327 


-0 . 00047 


-15.000 


-o.oo mo 


-0.00405 


-0 . 00478 


-0.00129 


-0.00450 


-0.00567 


-0.00356 


-10.000 


-0.00172 


-0.00376 


-0.00590 


-0.00415 


-0.00622 


-0.00701 


-0.00519 


-5.000 


-0.00134 


-0 . 00205 


-0.00405 


-0.00375 


-0.00510 


-0.00567 


-0.00468 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00217 


0.00273 


0.00375 


0.00695 


0.00936 


0.01077 


0.01220 


10.000 


0.00640 


0.01004 


0.01249 


0.01726 


0.02030 


0.02344 


0.02782 


15.000 


0.01072 


0.0177! 


0.02546 


0.03109 


0.03532 


0.03954 


0.04622 


20.000 


0.01775 


0.02984 


0.04353 


0.05229 


0.05742 


0.06243 


0.07330 



ENGINEER DgD 
OATE.yArJj--'2g 



FIGURE 4.1.1.2-23 

FFFECT OF ELEVON 



4.1.1.2-27 



si-:- occo im 



a 



Rockwell International 
Space Division 



MACH 



.15 



10 



< 

Q 



.05 



-.05 



Tl 



NUMBER 
I I l l 



5.000 



DELE CDEGD 

-50-25 25 

| I I i I | I l l I 1 I I I I 



I I I I I 



TTT 




I I I i 



I I 1 I i I! i 






Mil 



I I i I 



t^?d^^->^--- 



Mil 



I I M 



I I I M I I I I I I I II I I 



I...1.1. 



I I I II I I I 



-20 



-15 



■10 



5 10 

ALPHA CDEGD 



15 



20 



25 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIhCNSIONS 




CENTER OF GRAVITY XO « FS 1076. 7. IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE 20 - VI. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 



ENGINEER f 0-4-7$ 
DATE Z2£A____ 



FIGURE 



4.1.1.2 

EFFECT OF 



24 
ELEVON 




30 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCRD-C 


MT 






-*+0.000 


0.04347 


0.03677 


0.02830 


0.02219 


0.01462 


0.00997 


0.00816 


0.00720 


-35.000 


0.03447 


0.02863 


0.02270 


0.01576 


0.01093 


0.00739 


0.00560 


0.00494 


-30.000 


0.02573 


0.02248 


0.01710 


0.01173 


0.00671 


0.00480 


0.00304 


0.00319 


-25.000 


0.01949 


0.0167H 


0.01250 


0.00751 


0.00442 


0.00271 


0.00105 


0.00120 


-20.000 


0.01324 


0.01108 


0.00790 


0.00437 


0.00205 


0.00061 


-0.00094 


-0.00046 


-15.000 


0.00897 


0.00700 


0. 00420 


0.00156 


0.0 


-0.00094 


-0.00233 


-0.00239 


-10.000 


0.00391 


0.00300 


0.00120 


0.00014 


-0.00027 


-0.00250 


-0.00236 


-0.00493 


-5.000 


0.00089 


0.00021 


0.00060 


0.00002 


-0.00093 


-0.00125 


-0.00359 


-0.00478 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00258 


-0.00147 


0.00040 


0.00131 


0.00154 


0.00098 


0.00170 


0.00309 


10.00C 


-0.00287 


-0.00095 


0.00070 


0.00262 


0.00465 


0.00657 


0.00950 


0.01157 


15.000 


-0.00272 


0.00113 


0.00440 


0.00694 


0.00904 


0.01172 


0.01711 


0.02310 


20-000 


-0.00349 


0.00321 


0.00810 


0.01134 


0.01340 


0.02013 


0.02926 


0.04099 



4.1.1.2-28 



SD72-SH-CCCC 1M 



* 



Rockwell International 

Space Division 



NUMBER 

l I i l 



CDEGD 
o 



LU 

< 
u 
a 




25 30 35 

ALPHA CDEGD 



T 



CONFIGURATION 


BASELINE CRBITER VEHICLE 


REFERENCE DI^OSIONS 


CENTER OF GRAVITY XO » FS 107S.7 IN. 


UING AREA SW = 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MCfENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CU = 39.560 FT. 




BCOY LENGTH L3 = 1290.3 IN. 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (DEC) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON AXIAL FO 


RCE INCREhC 


sfT 






-40.000 


. 00997 


0.00816 


0.00720 


0.00799 


. 00693 


. 00S9O 


0.01280 


0.01869 


-35.000 


0.00739 


0.00560 


0.00494 


0.00525 


0.00336 


0.00417 


0.00827 


0.01524 


-30 . 000 


0.00480 


0.00304 


0.00319 


0.00251 


0.00075 


0.00185 


0.00554 


0.01168 


-25.000 


0.00271 


0.00105 


0.00120 


0.00022 


-0.00187 


-0.00112 


0.00237 


0.00825 


-20 . 000 


0.00061 


-0.00094 


-0.00046 


-0.00155 


-0.00343 


-0 . 00274 


0.00004 


0.00477 


-15.000 


-0.00094 


-0.00233 


-0 . 00239 


-0.00414 


-0 . 00657 


-0.00696 


-0.00361 


. 00265 


-10.000 


-0.00250 


-0.00236 


-0 . 00493 


-0.00463 


-0.00584 


-0.00592 


-0 . 00445 


-0.. 00 177 


-5.000 


-0.00125 


-0.00359 


-0 . 00478 


-0.00450 


-0.00475 


-0.00528 


-0.00600 


-0.00710 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


. 00098 


0.00170 


0.00309 


0.00459 


0.00615 


0.00769 


0.00910 


0.01064 


10.000 


0.00657 


0.00950 


0.01157 


0.01525 


0.01917 


0.02239 


0.02456 


0.02622 


15.000 


0.01172 


0.01711 


0.02310 


0.03135 


0.03619 


. 04058 


0.04658 


0.05399 


20.000 


0.02013 


0.02926 


0.04099 


0.05479 


0.06293 


. 07045 


0.08204 


0.09570 



ENGINEER DCo 
DATE„ter3ir~T2C 



FIGURE 



4. 1.1. 2-: 

EFFECT OF 



25 

ELEVON 



4.1.1.2-29 



SET 



i.-GCCC i M 



€> 



Rockwell International 

Space Division 



MACH NUMBER = 8. 000 

• i5i i "]■ -rry-rnn ri i i i i i i i i i i i i i i i i 



DELE CDEG) 

-50-25 £5 

IMF 



LU 

< 



.10 



.05 



-.05 



I I I I I I I 




I I I 1 



Mil 



I I I 



MM 



I i I I 



I I I I I I I I I I 



M M I I I I I 



I I I I I I I I I I I I I 



-20 



-15 



-10 



5 10 

ALPHA CDEGJ 



15 



20 



25 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WINS SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELE (DEG) 


A 


S 


C 





E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREME 


NT 






-HO. 000 


0.0H061 


0.03366 


0.02380 


0.01613 


0.00710 


0.00554 


0.00477 


0.00346 


-35.000 


0.033B5 


0.02740 


0.01890 


0.01276 


0.00555 


0.00377 


0.00296 


0.00261 


-3O.0OO 


0.02709 


0.02132 


0.01390 


0.00931 


0.00407 


0.00226 


0.00149 


0.00126 


-25.000 


0.02061 


0.01615 


0.01050 


. 00706 


0.00313 


0.00135 


0.00027 


0.00053 


-20.000 


0.01402 


0.01100 


0.00700 


0.00471 


0.00209 


0.00045 


-0.00038 


-0.00028 


-15.000 


0.00861 


0.00704 


. 00490 


0.00326 


0.00175 


0.00015 


0.00010 


-0.00113 


-10.000 


0.00321 


0.00306 


0-00280 


0.00200 


0.00123 


-0.00014 


-0.00127 


-0.00197 


-5.000 


0.00164 


0.00153 


0.00140 


0.00091 


0.Q0105 


-0.00015 


-0.00059 


-0.00082 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00278 


-0.00076 


0.00030 


0.00138 


0.00139 


0.00317 


0.00179 


0.00623 


10.000 


-0.00348 


-0.00152 


0.00050 


0.00266 


0.00434 


0.00635 


0.00790 


0.01213 


15.000 


-0.00388 


-0.00082 


0.00250 


0.00635 


0.00745 


0.01544 


0.01835 


0.03011 


20.000 


.-0.00607 


-0.00004 


0.00610 


0.01002 


0.01082 


0.02417 


0.03497 


0.04809 



ENGI 
DATE 



NEER DCo 



FIGURE 



4.1.1.2- 
EFFECT OF 



26 

ELEVON 



4.1.1.2-30 



\^ 



SCTS-SH-GCec JM 



€> 



Rockwell International 

Spaca Division 



L. 



MACH NUMBER 
• l5 n I I I I I I l I I I I 



8.000 



DELE CDEGD 

50 -25 25 

| I I I I | I I I I 



UJ 
< 

o 

Q 




-.05 



£5 30 35 

ALPHA CDEGD 



BASELINE 0RB1TER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - 8L 0.0 IN. 

MOMENT REFERENCE 20 = 14. 375.0 IN. 



AT ION 




REFERENCE DII-ENSIONS 




WING AREA SW - 8690.00 


SQ.FT. 


WING SPAN BW « 78.056 


FT. 


M.A.C. CW - 39.560 


FT. 


BODY LENGTH LB = 1390.3 


IN. 











ALPHA 


(OEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE tDEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON AXIAL FO 


RCE INGRES 


^rr 






-HO . 000 


0.00554 


0.00477 


. 00346 


. 00448 


0.00511 


0.00756 


0.01182 


0.01794 


-35.000 


0.00377 


0.00296 


0.00261 


0.00385 


0.00340 


0.0C556 


0.00937 


0.01495 


-30.000 


0.00226 


0.00149 


0.00126 


0.00322 


0.00247 


0.00470 


. 00865 


0.01433 


-25 . 000 


0.00135 


0.00027 


0.00053 


0.00243 


0.00066 


0.00166 


0.00517 


0.01078 


-20 . 000 


0.00045 


-0.00038 


-0.00028 


0.00164 


-0.00028 


0.00022 


0.00308 


. 00805 


-15.000 


0.00015 


0.00010 


-0.00113 


0.00003 


-0.00257 


-0.00325 


-0.00087 


0.00413 


-10.000 


-0.00014 


-0.00127 


-0.00197 


-0.00159 


-0.00413 


-0 . 00545 


-0.00470 


-0.00214 


-5.000 


-0.00015 


-0.00059 


-0.00082 


-0.00146 


-0.00348 


-0.00490 


-0.00499 


-0.00409 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00317 


0.00179 


0.00623 


0.00422 


0.00651 


0.00936 


0.01162 


0.01415 


10.000 


0.00635 


0.00790 


0.01213 


0.01475 


0.01785 


0.02198 


0.02712 


. 03420 


15.000 


0.01544 


0.01835 


0.03011 


0.03235 


0.03557 


0.04110 


0.05091 


0.06498 


20.000 


0.02417 


0.C3497 


0.04809 


0.05801 


0.06437 


0.07117 


0.08878 


0.11449 



ENGINEER OCo 
OATE.jA^Hr3>jgI 



FIGURE 4.1.1.2-57 

EFFECT OF ELEVON 



U. 1.1.2-31 



c 



-CCC C iM 



«L* 



Rockwell International 

Space Division 



MACH NUMBER 
• 15 ' I I I I | I I I i 



ui 

< 
u 

Q 




5 10 

ALPHA CDEGD 



COF I (JURATION 




8ASELINZ ORBITER VEHICLE 


REFERENCE DltOSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2590.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WINS SPAN BW - 78.055 


FT. 


MCrtNT REFERENCE ZO » WL 375.0 IN. 


M.A.C. CW " 39.560 


FT. 




BOOY LENGTH LB = 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL F0 


RCE INCREME 


NT 






-M0. 000 


0.04427 


0.03556 


0.02380 


0.01632 


0.00739 


0.00583 


0.00486 


0.00346 


-35.000 


0.03534 


0.02879 


0.01890 


0.01298 


0.00604 


0.00406 


0.00296 


0.00219 


-30.000 


0.02813 


0.02193 


0.01400 


0.00973 


0.00451 


0.00229 


0.00096 


0.00092 


-25.000 


0.02139 


0.01665 


0.01060 


0.00727 


0.00328 


0.00138 


0.00037 


0.00020 


-20.000 


0.01466 


0.01118 


0.00710 


0.00482 


0.00204 


0.00048 


-0.00032 


-0.00019 


-15.000 


0. 00938 


0.00741 


0.00480 


0.00310 


0.00125 


-0.00069 


-0.00168 


-0.00230 


-10.000 


0.00436 


0.00355 


0.00250 


0.00147 


0.00028 


-0.00150 


-0.00279 


-0.00484 


-5.000 


0.00125 


0.00177 


0.00120 


0.00073 


0.00028 


-0.00083 


-0.00152 


-0.00242 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00275 


-0.00085 


0.0 


0.00108 


0.00127 


0.00324 


0.00179 


0.00623 


10.000 


-0.00316 


-0.00161 


0.0 


0.00225 


0.00374 


0.00657 


0.00790 


0.01237 


15.000 


-0.00319 


-0.00072 


0.00250 


0.00623 


0.00722 


0.01541 


0.01835 


0.03026 


20.000 


-0.00587 


0.00016 


0.00630 


0.01011 


0.01080 


0.02424 


. 03469 


0.04773 



ENGINEERJPC© 
0ATE.^-j£^7jg 



FIGURE 



4.1.1.2- 

EFFECT OF 



28 

ELEVON 



4.1.1.2-32 



SE72-SH-0C6C 1M 



* 



Rockwell International 

Spaca Division 



MACH NUMBER 



10.000 



.15 



DELE CDEGD 

50-25 25 

T-TT-] 



.10 



LU 
< 
O 
Q 



.05 



I i I I I I I I i I I I II I I II I I I I 



-.051 I I I I I I I I I I I I [ 



- S «^i— r=«S£^tii|S 







10 15 20 25 30 35 

ALPHA CDEGD 



40 



45 



50 



55 



r 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DINCNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOtCNT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG1 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


DELE (C€G) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON AXIAL FO 


RCE INCREriE 


NT 






-HO . 000 


0.00583 


0.00486 


0.00346 


0.00372 


0.00498 


0.00813 


0.01236 


0.01782 


-35.000 


0.00406 


0.00296 


0.00219 


0.00344 


0.00335 


. 00560 


0.00913 


0.01406 


-30.000 


0.00229 


0.00096 


0.00092 


0.00265 


0.00112 


0.00244 


0.00576 


0.01114 


-25.000 


0.00138 


0.00037 


0.00020 


0.00201 


0.00042 


0.00144 


0.00436 


0.00918 


-20.000 


0.00048 


-0.00032 


-O.00C19 


0.00147 


-0.00052 


-0.00019 


0.00244 


0.00722 


-15.000 


-0.00069 


-0.00168 


-0.00230 


-0.00206 


-0.00462 


-0.00518 


-0.00370 


-0.00046 


-10.000 


-0.00150 


-0.00279 


-0.00484 


-0 . 00550 


-0.00790 


-0.00681 


-0.00811 


-0,00603 


-5.000 


-0 . 00083 


-0.00152 


-0.00242 


-0.00583 


-0.00713 


-0 . 00747 


-0.00721 


-0.00626 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00324 


0.00179 


0.00623 


0.00342 


0.00544 


. 00783 


0.00994 


0.01242 


10.000 


0.00657 


0.00790 


0.01237 


0.01507 


0.01847 


0.02255 


0.02669 


0.03177 


15.000 


0.01541 


0.01835 


0.03026 


0.03372 


0.03729 


0.04251 


0.05180 


0.06511 


20 . 000 


0.02424 


0.03469 


0.04773 


0.05758 


0.06391 


0.07071 


0.08874 


0.11520 



ENGINEER _PC« 



FIGURE 



4.1.1.2- 
EFFECT OF 



29 

ELEVON 



4.1.1.2-33 



cr - r. 



CCCC IM 



* 



Rockwell International 

Spac* DiviBton 



MACH 



,15 



,10 



< 
U 

o 



.05 



-.05 



NUMBER 

I II I 



15.000 



DELE 
-so -as 

i i i i 



CDEGD 
o 



25 



i_L 



I I I I 




till 



TTTT 



■^J^"?^^-'?^^^ 



i I ! i 



lilt 



=«fe- -t.t=^ 



i i li- 



lt i i 



TTT 



I I I I I I l l I I I 



J_J_ 



I I I I 




• ^ss* ^-p^S" 



I l l I 



I I l I 



I 1 1 



-20 



-15 



-10 



5 10 

ALPHA CDEG] 



15 



£0 



30 



CONFIGURATION 




BASELINE 0RBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE ZO • W_ 375.0 IN. 


M.A.C. ' CW - 39.560 


FT. 




BODY LENGTH LB ■ 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0ELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEV 


ON AXIAL FC 


RCE INCREPE 


NT 






-M0. 000 


0.04427 


0.03556 


0.02380 


0.01632 


0.00739 


. 00583 


0.00486 


. 00345 


-35.000 


0.03634 


0.02879 


0.01890 


0.01298 


0.00604 


0.00406 


0.002S6 


0.00219 


-30 . 000 


0.02813 


0.02193 


0.01400 


. 00973 


0.00451 


0.00229 


0.00096 


0.00092 


-25.000 


0.02139 


0.01665 


0.01060 


0.00727 


0.00328 


0.00138 


0.00037 


0*00020 


-20.000 


0.01466 


0.01118 


0.00710 


0.00482 


0.00204 


0.00048 


-0.00032 


-0.00019 


-15.000 


0.00938 


0.007H1 


0.00480 


0.00310 


0.00125 


-0.00069 


-0.00168 


-0.00230 


-10.000 


0.00436 


0.00355 


0.00250 


0.00147 


. 00028 


-0.00150 


-0.00279 


-0.00484 


-5.000 


0.00125 


0.00177 


0.00120 


0.00073 


0.00028 


-0.00083 


-0.00152 


-0.00242 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00275 


-0.00085 


0.0 


0.00108 


0.00127 


0.00324 


0.00179 


0.00623 


10.000 


-0.00316 


-0.00161 


0.0 


0.00225 


0.00374 


0.00657 


0.00790 


0.01237 


15.000 


-0.00319 


-0.00072 


0.00250 


0.00523 


0.00722 


0.01541 


0.01835 


0.03026 


20.000 


-0.00587 


0.00016 


. 00630 


0.01011 


0.01080 


0.02424 


0.03469 


.0.04773 



ENGINEER PCO 
OATE./JBL- grCgy 



FIGURE 



4.1.1.2- 

EFFECT OF 



30 

ELEVON 



4.1.1.2-34 



SD72-SH-0C60' IM 



J- 



* 



Rockwell International 

Space Division 



MACH NUMBER 
' l5 ' I l l i | I I i I 



15.000 



DELE COEGD 

-50 -25 25 

| I I i I | l I I I | I I I 

I I I I It i ! 1 I I I I I I I 



UJ 
< 

Q 




"I" 



25 30 35 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WIM3 SPAN SW - 78.056 FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB » 12S0.3 IN. 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


OELE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON AXIAL FO 


RCE INCREME 


MT 






-HO. 000 


0.005S3 


0.00486 


0.00346 


0.00372 


0.00438 


0.00813 


0.01236 


0.01782 


-35.000 


0.00406 


0.00296 


0.00219 


0.00344 


Q. 00335 


0.00560 


0.00913 


0.01406 


-30.000 


0.00229 


. 00096 


0.00092 


0.00265 


0.00112 


. 00244 


. 00576 


0.01114 


-25.000 


0.00138 


0.00037 


0.00020 


0.00201 


0.00042 


0.00144 


0.00435 


0.00918 


-20 . 000 


0.00048 


-0.00032 


-0.00019 


0.00147 


-0.00052 


-0.00019 


0.00244 


0.00722 


-15.000 


-0.00069 


-0.00168 


-0.00230 


-0.00206 


-0.00462 


-0.00518 


-0 . 00370 


-0.00045 


-10.000 


-0.00150 


-0.00279 


-0.00484 


-0.00550 


-0.00790 


-0.00881 


-0.00811 


-0.00603 


-5.000 


-0.00083 


-0.00152 


-0.00242 


-0.00583 


-0.00713 


-0.00747 


-0.00721 


-0.00626 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00324 


0.00179 


0.00623 


0.00342 


0.00544 


0.00783 


0.00994 


0.01242 


10.000 


0.00657 


0.00790 


0.01237 


0.01507 


0.01847 


0.02255 


0.02669 


0.03177 


15.000 


0.01541 


0.01835 


0.03026 


. 03372 


0.03729 


0.04251 


0.05180 


0.06511 


20.000 


0.02424 


0.03469 


0.04773 


0.05758 


0.06391 


0.07071 


0.08874 


0.11520 



ENGINEER^ CO 
OATEjlg-tf-?3. 



FIGURE 



4.1.1.2- 

EFFECT OF 



31 

ELEVON 



4.1.1.2-35 






-SH-CC6 IM 



*> 



Rockwell International 

Space Division 



MACH 



.15 



.10 



< 
a 



.05 



TT 



NUMBER 
TTTT 



20.000 



-50 



DELE 

-25 



CDEGD 
o 



25 



TT 




I I I I 



III. 



TT 



<fr W^tEuL. 'Xj. 1 *- 



5=?33& 



TT 



j i ^'p^ iiia 



I I I 



TTT 



i i I I 




-.(fil I I I 1 I I I I I I I I I i I i i i i I i i i i I i 

-20 -15 -10-5 5 10 



I I I I I I I I I I I l I I 



TTTT 



I I I I 



15 



20 



25 



30 



ALPHA CDEGD 









CONFJGURATIC 


BASELINE ORBITER VEHICLE 




CENTER OF GRAVITY 


XO 


- FS 


1075.7 


IN. 


OR 


YO 


- BL 


0.0 


IN. 


MCf€NT REFERENCE 


ZO 


- WL 


375.0 


IN. 



VTIGN 




REFERENCE DIMENSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BUI - 78.056 


FT. 


M.A.C. CW « 39.560 


FT. 


9COY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 





E 


F 


G 


H 






ELEV 


ON AXIAL FO 


RCE INCREME 


NT .J 






-HO. 000 


0.04427 


0.03556 


0.02380 


0.01632 


0.00739 


0.00583 


0.00486 


0.00346 


-35.000 


0.03634 


0.02879 


0.01890 


0.01298 


0.00604 


0.00406 


0.00296 


0.00219 


-30.000 


0.02813 


0.02193 


0.01400 


0.00973 


0.00451 


0.00229 


0.00095 


0.00092 


-25.000 


0.02139 


0.01665 


0.01060 


0.00727 


0.00328 


0.00138 


0.00037 


0.00020 


-20.000 


0.01466 


0.01118 


0.00710 


0.00482 


0.002O4 


0.00048 


-0.00032 


-0.00019 


-15.000 


0.00938 


0.00741 


0.00480 


0.00310 


0.00125 


-0.00069 


-0.00168 


-0.00230 


-10.000 


0.00436 


0.0C355 


0.00250 


0.00147 


0.00028 


-0.00150 


-0.00279 


-0.00484 


-5.000 


0.00125 


0.00177 


0.00120 


0.00073 


0.00028 


-0.00083 


-0.00152 


-0.00242 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-O. 00275 


-0.00085 


0.0 


0.00108 


0.00127 


0.00324 


0.00179 


0.00623 


10.000 


-0.00316 


-0.00161 


0.0 


0.00225 


0.00374 


0.00657 


0.00790 


0.01237 


15.000 


-0.00319 


-0.00072 


0.00250 


0.00623 


0.00722 


0.01541 


0.01835 


0.03026 


20.000 


-0 . 00587 


0.00016 


0.00630 


0.01011 


0.01080 


0.02424 


0.03469 


0.04773 



engineer dco 
oatc./a5S«: 



FIGURE 



4.1.1.2- 

EFFECT OF 



32 
ELEVON 



4.1.1.2-36 



\~s 



SE72-SK-C06 1M 



* 



Rockwell International 

Space Division 



3_. 



MACH NUMBER 
• 15 i l i i I I I l l I i i i i i i i 



20.000 



DELE CDEGD 

-50 -25 25 

I i I I | I I I I | I I ! I 

I I I I 



< 

u 

a 




-.05 



i i i t I i i i i I i i i i I i i i l I i i i i 



10 



15 



20 



25 30 35 

ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOtNT REFERENCE ZO ■ U. 375.0 IN. 



REFERENCE DIfCNSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW - 78.056 


FT. 


M.A.C. CW - 39.560 


FT. 


BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40 . 000 


45.000 


50.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEV 


ON AXIAL FO 


RCE INCREME 


vJT 






-HO. 000 


0.00583 


. 00486 


0.00346 


0.00372 


0.00498 


0.00813 


0.01236 


0.01782 


-35.000 


. 00406 


0.00296 


0.00219 


. 00344 


0.00335 


0.00560 


0.00913 


0.01405 


-30.000 


. 00229 


. 00096 


0.00092 


0.00265 


0.00112 


0.00244 


0.00575 


0.01 114 


-25.000 


0.00138 


0.00037 


0.00020 


0.00201 


0.00042 


0.00144 


. 00436 


0.00918 


-20 . 000 


0.00048 


-0.00032 


-0.00019 


0.00147 


-0.00052 


-0.00019 


0.00244 


. 00722 


-15.000 


-0.00069 


-0.00168 


-0.00230 


-0.00206 


-0 . 00462 


-0.00518 


-0 . 00370 


-0.00C46 


-10.000 


-0.00150 


-0.00279 


-0.00484 


-0.00550 


-0 . 00790 


-0.00881 


-0.00811 


-0 . 00603 


-5.000 


-0.00083 


-0.00152 


-0.00242 


-0.00583 


-0.00713 


-0.00747 


-0.00721 


-0 . 0062b 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00324 


0.00179 


0.00623 


0.00342 


0.00544 


0.00783 


0.00994 


0.01242 


10.000 


0.00657 


0.00790 


0.01237 


0.01507 


0.01847 


0.02255 


0.02669 


0.03177 


15.000 


0.01541 


0.01835 


0.03026 


0.03372 


0.03729 


0.04251 


0.05180 


0.06511 


20.000 


0.02424 


0.03469 


0.04773 


0.05758 


0.06391 


0.07071 


0.08874 


0. 1 1520 



ENGINEER QC.O 
OATEj.Q-:^.rZi- 



FIGURE 



4.1.1.2- 

EFFECT OF 



33 

ELEVON 



4.1.1.2-37 



c 






cccc 



i M 



a 



Rockwell International 

Space Division 



VBAR 



0.005 



DELE CDEG) 

50 -25 25 



.08 



LU 

< 
O 
Q 




25 30 35 

ALPHA CDEG3 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE Dir-ENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - a. 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MO>€NT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 



DELE (DEG) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (PEG) 



20.000 
A 



25.000 
B 



30.000 
C 



35.000 




40.000 

E 



45.000 

F 



50.000 
G 



ELEVON AXIAL FORCE INCRE^EKT 



0.00486 


0.00346 


0.00296 


0.00219 


0.00096 


0.00092 


0.00037 


0.00020 


0.00032 


-0.00019 


0.00168 


-0.00230 


0.00279 


-0.00484 


0.00152 


-0.00242 


0.0 


0.0 


0.00179 


0.00623 


0.00790 


0.01237 


0.01835 


0.03026 


0.03469 


0.04773 



ENGINEER MSA 
DATE " 



FIGURE 



0.00372 

0.00344 

0.00255 

0.00201 

0.00147 

-0.00206 

-0.00550 

-0.00583 

0.0 

0.00342 
0.01507 
0.03372 
0.05758 



0.00498 

0.00335 

0.00112 

0.00042 

-0.00052 

-0.00462 

-0.00790 

-0.00713 

0.0 

0.00544 
0.01847 
0.03729 
0.06391 



0.00813 

0.00560 

0.00244 

0.00144 

-0.00019 

-0.00518 

-0.00881 

-0.00747 

0.0 

0.00783 
0.02255 
0.04251 
0.07071 



0.01236 

0.00913 

0.00576 

0.00436 

0.00244 

-0.00370 

-0.00811 

-0.00721 

0.0 

0.00994 
0.02669 
0.051.80 
0.08874 



0.01782 
0.01406 
0.01114 
0.00918 
. 00722 
0.00046 
0.00603 
00626 


01242 
03177 
06511 
11520 



4. 1. 1 

EFFECT 



2-34 

OF ELEVCN 



4.1.1.2-38 



SCTf-SH-CCGC 1M 



a 



Rockwell International 

Space Division 



L 



LU 

< 



DELE CDEG) 
-50 -as 25 

i i i i 




30 35 

ALPHA CDEGD 



COfflGLRATlON 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO - FS 107S.7 IN. 
OR YD - BL 0.0 IN. 

MO€NT REFERENCE 20 - WL 375.0 IN. 



REFERENCE OlfENSICNS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB ■ 1390- 3 IN. 





ALPHA <OEG) 






20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 






ELEVON AX 


IAL FORCE I 


NCRETCNT 






-HO . 000 


. 00486 


0.00346 


0.00372 


0.00498 


0.00313 


0.01236 


0.01782 


-35.000 


0.00296 


0.00219 


0.00344 


0.00335 


. 00550 


0.00913 


0.01406 


-30 . 000 


0.00096 


. 00092 


0.00265 


0.00112 


0.00244 


0.00575 


0.01114 


-25.000 


. 00037 


0.00020 


0.00201 


0.00042 


0.00144 


0.00436 


0.00918 


-20 . 000 


-0.00032 


-0.00019 


0.00147 


-0.00052 


-0.00019 


.0.00244 


. 00722 


-15.000 


-0.00168 


-0.00230 


-0.00206 


-0 . 00462 


-0.00518 


-0 . 00370 


-0.00046 


-10.000 


-0.00279 


-0.00484 


-0.00550 


-0.00790 


-0.00881 


-0.00811 


-0.00603 


-5.000 


-0.00152 


-0.00242 


-0.00583 


-0.00713 


-0.00747 


-0.00721 


-0 . 00626 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


.0.0 


5.000 


0.00179 


0.00623 


0.00342 


0.00544 


0.00783 


0.00994 


0.01242 


10.000 


0.00790 


0.01237 


0.01507 


0.01847 


0.02255 


0.02669 


0.03177 


15.000 


0.01835 


0.03026 


0.03372 


0.03729 


0.04251 


0.05180 


0.06511 


20.000 


. 03469 


0.04773 


0.05758 


0.06391 


0.07071 


0.08874 


0.1 1520 



ENGlh£ER NASA. 
DATE 



FIGURE 4.1.1.2-35 

EFFECTOFELEVON 



4.1.1.2-39 






CCcC 1M 




Rockwell International 

Span Division 



ALTITUDE CFT.3' = 300,000 to 600,000 



$ 



12 



,10 



.08 



.06 



.OH 



.02 



.02 



MM 



^^^re 




I I 



I 1 l l 



l I I l 



I I I I 



l l l l 



III! 



■ Mil 



10 



15 



20 



30 

ALPHA 



35 

CDEGD 



HO 



H5 



50 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE OI^€NSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


MING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU » 78.055 


FT. 


MCfENT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 



ENGINEER. NAgA„ 
OATE 





ALPHA (DEC) 


20.000 


25.000 


30.000 


35.000 


HO. 000 


H5.000 


50.000 


DELE (OEG) 


A 


8 


C 


D 


E 


F 


G 






ELEVON AX 


IAL FORCE 1 


NCRQCNT 






-HO. 000 


0.OOH8S 


0.003H6 


0.00372 


0.0OH98 


0.00813 


0.01236 


0.01782 


-35.000 


0.00296 


0.00219 


0.003HH 


0.00335 


0.00560 


0.00913 


0.01H06 


-30.000 


0.00096 


0.00092 


0.00255 


0.00112 


0.002HH 


0.00576 


0.01IIH 


-25.000 


0.00037 


0.00020 


0.00201 


0.0OOH2 


0.001H4 


O.0OH36 


0.00918 


-20.000 


-0.00032 


-0.00019 


0.001H7 


-0.00052 


-0.00019 


0.002HH 


0.00722 


-15.000 


-0.00168 


-0.00230 


-0.00206 


-0.0OH62 


-0.00518 


-0.00370 


-O.00OH6 


-10.000 


-0.00279 


-0.00H8H 


-0.00550 


-0.00790 


-0.00881 


-0.00811 


-0.00603 


-5.000 


-0.00152 


-0.002H2 


-0.00583 


-0.00713 


-0.007H7 


-0.00721 


-0.00626 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00179 


0.00623 


0.003H2 


0.005HH 


0.00783 


0.0099H 


0.012H2 


10.000 


0.00790 


0.01237 


0.01507 


0.018H7 


0.02255 


0.02669 


0.03177 


15.000 


0.01835 


0.03026 


0.03372 


0.03729 


0.0H251 


0.05180 


0.06511 


20.000 


0.03H69 


0.0H773 


0.05758 


0.06391 


0.0707! 


0.0887H 


0.11520 


ISA 


FIG 


WE 4. ] 


1.1.2-36 











EFFECT OF ELEVON 



55 



V^ 



4.1.1.2-40 



SE72-SK-0C60 1M 



€> 



Rockwell International 

Spaca Division 



MACH NUMBER 
■P^ i l l l I I I I i l 



0.250 



DELBF CDEGD 

-25 25 



03 

< 

a 




CONFIGURATION 



BASELINE ORB1TER VEHICLE 

CENTER OF GRAVITY XO = FS 107S.7 IN. 

OR YO " BL 0.0 IN. 

MCTENT REFERENCE 20 - W_ 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 




DELBF (PEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



BODY FLAP AXIAL FORCE INCREMENT 



0.00790 

0.00197 

0.0 

0.00238 

0.00475 

0.00774 

0.01375 



0.00675 

0.00185 

0.0 

0.00004 

0.00157 

. 00464 

0.01014 



. C0590 
0.00170 
0.0 
-0 . 00054 
0.00013 
. 00300 
. 00820 



0.00522 
0.00145 
0.0 
-0 . 00042 
0.00026 
0.00340 
0.00825 



0.00510 
0.00135 
0.0 
-0.00032 
0.00048 
0.00417 
0.00943 



0.00838 
. 00235 
0.0 
-0.00073 
0.00028 
0.00506 
0.01203 



0.01158 
0.00334 
0.0 
-0.001 16 
-0.00001 
0.00568 
0.01474 



0.01415 
0.00450 
0.0 
-0.0C240 
-0 . 00257 
0.00129 
. 00732 



ENGINEER \j~r*7- 

OATE ~.£iyjzD* 



FIGURE 4.1.1.2-37 

EFFECT OF BODY FLAP 



4.1.1.2-41 



L 



C iM 



Rockwell International 

SpanDivMon 



I 



MACH NUMBER 

•"♦M I I I I I I I 



0.400 



DELBF CDEGD 

-25 25 



Ll 

m 

< 



.03 



.02 



.01 



-.01 



I I 1 I 



■15 



I I I I 



I I | I I I I I I I I 1 I I I I I 



J_L 




TT 



I I I I 



I I I I 



I I I 



Mir 



_L_L 



■10 



5 
ALPHA 



10 
CDEGD 



15 



20 



30 



CONFIGURATION 




BASELINE 0R81TER VEHICLE 


REFERENCE OII-ENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCtCNT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CU - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELBF <C€G) 


A 


B 


C 





E 


F 


G 


H 






BCOY 


FLAP AXIAL 


FORCE INCRE1 


h€NT 






-11.700 


0.00780 


0.00675 


0.00590 


0.00522 


0.00510 


0.00838 


0.01158 


0.01415 


-5.000 


0.00197 


0.00185 


0.00170 


0.00145 


0.00135 


0.00235 


0.00334 


0.00450 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00238 


0.00004 


-0.00054 


-0.00042 


-0.00032 


-0.00073 


-0.00116 


-0.00240 


10.000 


0.00475 


0.00157 


0.00013 


0.00026 


0.00048 


0.00023 


-0.00001 


-0.00257 


16.300 


0.00774 


0.00464 


0.00300 


0.00340 


0.00417 


0.00506 


0.00568 


0.00129 


22.500 


0.01372 


0.01014 


0.00820 


0.00825 


0.00943 


0.01203 


0.01474 


0.00792 



ENGINEER 
OATE I 



UjmL 



FIGURE 4.1.1.2-38 

EFFECT OF BODY FLAP 



4.1.1.2-42 



SD7 



»~ /~i ^ 

1 -L-V/O 



iM 



'1* 



Rockwell International 

Spac« Division 



MACH NUMBER 
•° H i i i | I I l M l 



0.600 



DELBF CDEGD 

25 25 

I I I | I I I I 



U. 

ca 
< 
u 

Q 




.01 
-15 



I I I I 



_L_L 



M il 



J_J_ 



I I I 



iill 



I I I I 



r^^rT 



J_L I ,1 



-10 



5 

ALPHA 



10 
CDEG] 



15 



20 



25 



30 



CONFIGURATION 



BASELINE 0R8ITER VEHiaE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIt-ENSICNS 

WING AREA SW = 2690.00 SQ.FT. 

WING SPAN BW = 79.056 FT. 

M.A.C. CW = 39.560 FT. 

BOOY LENGTH LB - 1290.3 IN. 



CELBF <C£G> 


ALPHA (C€G) 








-10.000 
A 


-5.000 
8 


0.0 
C 


5.000 
O 


10.000 
E 


15.000 

F 


20.000 
G 


25.000 
H 






9COY 


FLAP AXIAL FORCE INCREl 


-ENT 






-11.700 
-5.000 
0.0 
5.000 
10.000 
16.300 
22.500 


. 0054 ! 

0.00107 

0.0 

0.00273 

0.00566 

0.00939 

0.01308 


. 00548 

0.00138 

0.0 

0.00010 

0.001H7 

0.00548 

0. 01234 


0.00563 
0.00144 
0.0 
-0.00008 
0.00126 
0.00530 
0.01202 


. 00552 
0.00138 
0.0 
-0.00003 
0.00138 
0.00561 
0.01266 


0.00456 

0.00106 

0.0 

0.00015 

0.00172 

0.00573 

0.01184 


. 00250 

0.00011 

0.0 

0.00146 

0.00437 

0.00959 

0.01625 


-0.00038 
-0.00082 
0.0 

0.00294 
0.0C595 
0.00949 
0.01281 


-0.00155 
-O.COl 1 1 
0.0 

0.001S6 
. 0D455 
0.C0822 
0.01223 



ENGINEER U»*"Z- 
DATE ZZiYki'll 



FIGURE 4.1.1.2-39 
EFFECT OF BODY FLAP 



4.1.1.2-43 



c r r ' 



C C C C ! M 



# 



MACH NUMBER 



0.800 



CD 

< 



.04 



.03 



.02 



.01 



Rockwell International 

Space Division 

L 



DELBF CDEGD 
-25 q 25 

I I I I l I I I 



-.01 



I I I I I I I I I I 



.1. L. I I 



i i i i I i i i i I i i i i i 'i r i i 




i ,i 



_l I L_ 



1J.-1. 



m liii 



-i_L 



1 I I 



-15 



-10 



5 
ALPHA 



10 
CDEGD 



15 



-20 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIfENSIONS 




CENTER OF GRAVITY XO - F5 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 6W = 78.056 


FT. 


MCtCNT REFERENCE ZO - W. 375.0 IN. 


H.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


(CEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP AXIAL 


FORCE INCRE 


hENT 






-11.700 


0.00551 


0.00608 


0.00735 


. 00767 


0.00664 


0.00453 


0.00146 


0.00319 


-5.000 


0.00111 


0.00148 


0.00144 


0.00189 


0.00>49 


0.00065 


-0.00037 


0.00014 


0.0 


0.0 


0.0 


0.0 


0.0 


O.U 


0.0 


0.0 


0.0 


5.000 


0.00265 


0.00028 


0.00319 


. 00028 


0.00068 


0.00128 


0.00201 


0.00234 


10.000 


0.00553 


0.00217 


0.00830 


0.00266 


0.00341 


0.00459 


0.00558 


0.00629 


16.300 


0-00922 


0.00675 


0.01291 


0.00832 


0.00923 


0.01102 


0.01151 


0.01216 


22.500 


0.01294 


0.01387 


0.01494 


0.01664 


0.01735 


0.01954 


0.01868 


0.01876 



ENGINEER \jJ\M% 
DATE ZZ A-ilnt 



FIGURE 4.1.1.2-40 
EFFECT OF BODY FLAP 



V^ 



4.1.1.2-44 



SD72-SH-C06C 1M 



<!> 



Rockwell International 

Spac« Division 



MACH NUMBER 



.04 



0.900 



"I l I I I l 



03 
< 
O 
Q 



1 ' < M i I h I | i | | I j i | , 



OELBF CDEGJ 

"gS , 25 

T I ! T 



T'l TT 
I I II 




CONFIGURATION 



BASELINE 0R81TER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MOMENT REFERENCE ZO = U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 5690.00 SQ.FT. 
WING SPAN BUI = 7B.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB » 1390.3 IN. 



CELBF (DEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



-10.000 
A 



-5.000 
B 



0.0 

c 



ALPHA (DEG) 



5.000 




10.000 
E 



15.000 

F 



0.00645 

0.00143 

0.0 

0.00127 

0.00436 

0.00914 

0.01459 



0.00742 

0.00191 

0.0 

0.00021 

0.C0215 

0.00689 

0.01414 



BOOY FLAP AXIAL FORCE INCREMENT 



20.000 
G 



£5.000 
H 



0.00904 
0.00215 
0.0 
-0.00027 
0.00136 
0.00632 
0.01443 



0.00816 
. 00208 
0.0 
-0.00013 
. 00208 
0.00791 
0.01689 



. 00720 

0.00168 

0.0 

0.00027 

0.00269 

0.00888 

0.01835 



. 00532 

. 00087 

0.0 

0.00174 

0.00558 

0.01178 

0.01914 



0.00308 

0.0 

0.0 

0.00340 

0.00782 

0.01356 

0,01945 



. 00205 
-0 . 00048 
0.0 

0.00444 
. 00983 
0.01549 
0.01985 



ENGINEER JitfM-J. 
DATE. ~.5-ZtJ.-"»» 



FIGURE 4.1.1.2-41 

EFFECT OF RHPY FLAP 



4.1.1.2-45 



SL71' -SH-CC6C IM 




Rockwell International 

SpacvOivMon 



MACH NUMBER = 0.950 

• 0H| ' i I I | i I I I | i i i i | i i I i I I i i i 1 i i i i | ; i i i 



DELBF CDEGD 

-25 25 



Li. 
GQ 

< 



.03 



.02 



.01 



.0 



.01 



I I I I 



I 1 I I 



I I I I 



_L 



_L_L 




J__L 



l l l 



I I I I I 1 I I 



I I I I I I I I I 



—L— 1 — ! 



JL_L 



-15 



-10 



5 
ALPHA 



10 

CDEG3 



15 



=■20 



25 



30 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIf-CNSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MCt€NT REFERENCE ZO « WL 375.0 IN. 


M.A.C. CW ■ 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






BCOY 


FLAP AXIAL 


FORCE INCRE1 


h€NT 


1 




-11.700 


0.00748 


0.00757 


0.00726 


0.00654 


0.00588 


0.00361 


0.00257 


-0.00031 


-5.000 


0.0019B 


0.00199 


0.00166 


0.00150 


0.00125 


0.00046 


0.00011 


-0.00079 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00002 


0.00052 


0.00203 


0.00021 


0.00040 


0.00115 


0.00138 


0.00175 


10.000 


0.00174 


0.00280 


0.00521 


0.00241 


0.0C267 


0.00394 


0.00430 


0.00456 


16.300 


0.00608 


0.00691 


0.00948 


0.00854 


0.00895 


0.00983 


0.00981 


0.00938 


22.500 


0.01268 


0.01210 


0.01398 


0.01847 


0.01916 


0.01821 


0.01638 


0.01374 



ENGINEER tyiviT. 
OATE ."_$-JLL-")« 



FIGURE 4.1.1.2-42 

EFFECT OF BODY FLAP 



4.1.1.2-46 



SD72-SH-CC6C IM 



*1% 



Rockwell International 

Spaca Division 



MACH NUMBER = 0.980 

• 04 | I i l I I I i l I I I r 



DELBF CDEG3 

-25 25 

I l I II I 



U. 

< 
u 

Q 




CONFIGURATION 



BASELI^ ORBITER VEHICLE 

CENTER OF GRAVITY XO - F5 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOTCNT REFERENCE 20 = UL 375.0 IN. 



REFERENCE Dir-ENSIONS 

WING AREA SW « 2690.00 SQ.FT. 

WING SPAN BW = 78.056 FT. 

M.A.C. CW =■ 39.550 FT. 

BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 




-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF CDEG) 


A 


B 


C 





E 


F 


G 


H 






BODY 


FLAP AXIAL FORCE INCRE 


tNT 






-11.700 


0.00716 


0.00771 


0.00698 


0.00600 


0.00552 


0.00358 


0.00329 


0.00088 


-5.000 


0.00192 


0.00198 


0.00154 


0.00124 


0.00103 


0.00036 


0.00026 


-0.00051 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00016 


. 00062 


0.00217 


0.00063 


0.00074 


0.00134 


0.00136 


. 00 1 72 


10.000 


0.00139 


0.00304 


0.00548 


0.00323 


0.00347 


. 00444 


0.00442 


0.00475 


16.300 


. 00554 


0.00713 


0.00989 


0.00965 


0.01037 


0.01102 


0.01103 


0.01085 


22.500 


0.0119H 


0.01228 


0.01452 


0.01950 


0.02114 


. 02C48 


0.01S95 


0.01577 



ENGII^ER UumX. 

0ATE ^L-.iis'rt 



FIGURE 4.1.1.2-43 

EFFECT GF BODY FLAP 



4.1.1-2-47 



U 



i!i-CCC:C 1M 



tfl 



Rockwell International 
Spaca Division 



MACH NUMBER 



1.050 



DELBF CDEG) 

25 25 

mr 



CD 

< 

8 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - U- 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN 8W - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 












ALPHA (DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP AXIAL FORCE 1NCREI 


"ENT 






-11.700 


0.00736 


0.00729 


0.00694 


0.00570 


0.00566 


0.00401 


0.00451 


0.00363 


-5.000 


0.00193 


0.00180 


0.00153 


0.00082 


0.00051 


0.00006 


0.00033 


0.00014 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00050 


0.00045 


0.00098 


0.00218 


0.00357 


0.00271 


. 00229 


0.00218 


10.000 


0.00254 


0.00285 


0.00409 


0.00667 


0.00943 


0.00785 


0.00694 


0.00658 


16.300 


0.00629 


0.00780 


0.00996 


0.01404 


0.01820 


0.01687 


0.01549 


0.01449 


22.500 


0.01126 


0.01459 


0.01760 


0.02290 


0.02889 


0.02862 


0.02S62 


0.02436 



ENGINEER_i*-*iV 
OATE 3L--liir*>g 



FIGURE 4.1.1.2-44 

EFFECT OF BODY FLAP 



KS 



4.1.1.2-48 



SE72-SH-CC6C IM 



€> 



Rockwell International 

Space Division 



CD 
< 
CJ 

o 



MACH 



.04 



.03 



.02 



.01 



I I I I 



NUMBER 
I I I I 



Oil— L 
-15 



J_L 



i I I I 



1. 100 

MM 



OELBF CDEG) 

-25 25 

| l I I I | M I ! f 



I I I i 



I I I I 



I I I 




1 111 



I I I I 



I I I I 



I I I I 



lilt 



MIT 



J_X_L_L 



_LJ__L_L 



I .I , I . !_ 



-10 



5 

ALPHA 



10 

CDEG 3 



15 



20 



25 



30 



COF I ORATION 


BASELINE 0RSITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MOMENT REFERENCE ZO - M. 375.0 IN. 


M.A.C. CW • 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA CDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF <CEG> 


A 


B 


c 


O 


E 


F 


G 


H 






ecoY 


FLAP AXIAL FORCE INCRE 


^CNT 






-11.700 


0.00698 


0.00642 


. 00654 


0.00501 


0.00524 


0.00418 


. 00479 


. 00462 


-5.000 


0.00177 


0.00149 


0.00137 


0.00045 


0.00014 


-0.00002 


0.00035 


. 0004 1 


o-.o 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00074 


0.00057 


0.00094 


0.00313 


0.00539 


0.00321 


0.00240 


0.00199 


10.000 


0.00298 


0.00304 


. 00403 


0.00842 


0.01222 


0.00907 


0.00734 


0.00631 


16.300 


0.00683 


0.00826 


0.01031 


0.01610 


0.02127 


0.01869 


0.01648 


0.01481 


22.500 


0.01175 


0.01551 


0.01890. 


0.02459 


0.03142 


0.03113 


. 02878 


0.02541 



ENGINEER t/giwvV 
OATE AjXl-")* 



FIGURE 4.1.1.2-45 
EFFECT OF BODY FLAP 



4.1.1.2-49 



r72~LH-ocec 1M 



4* 



Rockwell International 

Space Division 



MACH NUMBER 
•<*| l I I I I I I I I 



1.200 



DELBF CDEGD 

-25 25 



U. 

in 
< 
u 

Q 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO » BL 0.0 IN. 

MOMENT REFERENCE ZO - VL. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW ' 39.560 FT. 

BODY LENGTH LB " 1290-3 IN. 



DELBF (PEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



ALPHA (DEC) 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
D 



10.000 

E 



15.000 

F 



20.000 
G 



25-000 
H 



BCOY n AP AXIAL FORCE INCREMENT 



0.00452 

0.00087 

0.0 

0.00076 

0.00296 

0.00816 

0.01633 



0.00329 

0.00031 

0.0 

0.00200 

0.00S37 

0.01033 

0.015SO 



0.00227 
-0.00012 
0.0 

0.00271 
0.00653 
0.01168 
0.01710 



0.00150 
-0 - 00065 
0.0 

0.00313 
0.00807 
0.01551 
0.02394 



0.00174 
-0.00065 
0.0 

0.00354 
0.00892 
0.01672 
. 02533 



0.00313 
-0.00012 
0.0 

0.00245 
0.00704 
0.01557 
0.02698 



0.00410 

0.00037 

0.0 

0.00146 

0.00502 

0.01318 

0.02536 



0.00423 

0.00061 

0.0 

0.00056 

0.00294 

0.01039 

0.02321 



ENGINEER .£/>*£. 
DATE „_„3.rJll-'> 8 



FIGURE 4.1.1.2-46 

FFFFPT flF BODY FLAP 



\S 



4.1.1.2-50 



£E72-SH-OCeC 1M 



4L* 



Rockwell International 

Space Division 



X 



MACH NUMBER 



1.300 



DELBF CDEG) 

-25 25 

[ I I I I | I I I I 
III! 



00 

< 

8 




CONFIGURATION 



BASELINE ORB1TER VEHICLE 

CENTER OF GRAVITY XO » FS 1075.7 IN. 

OR YO » BL 0-0 IN. 

MOENT REFERENCE ZO - WL 375. C IN. 



REFERENCE DlfENSIONS 
WING AREA SW = 3590.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 8390.3 IN. 



DELBF (PEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
23. 500 



ALPHA (DEG) 




-5 . 000 
8 



0.0 
C 



5.000 
O 



10.000 
E 



15.000 
F 



20 . 000 
G 



25.000 
H 



BCCY FLAP AXIAL FORCE INCREMENT 



. 00603 

0.00150 

0.0 

0.00093 

0.00308 

0.00631 

0.01002 



0.00488 

0.00108 

0.0 

0.0007H 

0.00290 

0.00701 

0.012H2 



0.00300 

0.00042 

0.0 

0.00075 

0.00274 

0.00752 

0.01498 



0.00192 
-0.00017 
0.0 

0.00158 
. 00468 
0.01086 
0.01944 



0.00218 
-0 . 00045 
0.0 

0.00471 
. 00944 
0.01577 
0.03269 



0.00076 
-0.00087 
0.0 

0.00472 
0.00913 
0.01530 
0.02303 



0.00035 
-0.00110 
0.0 

0.00503 
0.01011 
0.01648 
. 03280 



-0 . 00037 
-0.00134 
0.0 

0.00485 
0.01052 
0.01663 
0.02146 



ENGINEER U«w"Z- 
DATE "3rXL-J« 



FIGURE 4.1.1.2-47 

EFFECT CF BODY FLAP 



4.1.1.2-51 



E72 



■CCtC 1M 



#JI 



Rockwell International 

Spac* Division 



MACH NUMBER 



1.500 



u. 

CD 

< 

8 



.04 



.03 



.02 



.01 



.01 



it r 



-*^3C 



I I I I 



,1 I I J. 



1 I i 



11 1 1 



m r~m i i i i i i i i 



i i 




J_L 



DELBF CDEGD 

-25 25 

| 1 ! I I | i I I I ( 

I I I I I I I 



L 1 I 



1 i I 



1 I I I 



■15 



-10 



5 
ALPHA 



10 

CDEGD 



15 



20 

■a 



25 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW « 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOCNT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB « 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 


H 






BODY 


FLAP AXIAL 


FORCE INCRE 


MENT 






-11.700 


0.00083 


0.00089 


0.00149 


0.00146 


0.00100 


0.00378 


0.00497 


0.00620 


-5.000 


-0.00012 


-0.00015 


-0.00014 


-0.00041 


-0.00061 


-0.00002 


0.00029 


0.00057 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00136 


. 00097 


0.00180 


. 00369 


0.00402 


0.00510 


0.00531 


0.00540 


10.000 


0.00315 


0.00274 


0.00455 


0.00733 


0.00770 


0.01046 


0.01113 


0.01237 


16.300 


0.00540 


0.00597 


0.00846 


0.01208 


0.01271 


0.01703 


0.01806 


0.01974 


22.500 


0.00754 


0.01020 


0.01272 


0.01718 


0.01875 


0.02394 


0.02531 


0.02613 



ENGINEER 1*^3. 
DATE "3:AL-"» 



FIGURE 4. 1.1.2 -h8 

EFFECT OF BODY FLAP 



4.1.1.2-52 



c i 



';-<• Co" !M 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



2.000 



OELBF CDEG) 
-as 25 



CD 

< 
(J 
a 




.01 
-15 



I I I I I I I I ! I I I ! I I I I I I I I I I I I I I 1 I I I I I I 1 I I. 1 - 1 I I I I I l-i-L-l 

-10 -5 5 10 15 20, 25 30 35 

ALPHA CDEG 3 











CONFI 


GURA1 


BASEL IS£ ORBITER 


VEHICLE 






CENTER 


CF GRAVITY 


XO 


- FS 


1075 


7 


IN. 




OR 


YO 


» BL 








IN. 


MOf"ENT 


REFERENCE 


ZO 


- WL 


375 





IN. 



TION 




REFERENCE OirENSICNS 




WING AREA SW = 2690.00 


SQ.FT. 


WING SPAN BW « 78.056 


FT. 


M.A.C. CW = 39.560 


FT. 


BOOY LENGTH LB » 1290.3 


IN. 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


30 . 000 


DELBF (DEG) 


A 


S 


C 


D 


E 


F 


G 


H 


I 








BCOY FLAP AXIAL FCRCE 


INCREMENT 








-11.700 


-0.00035 


-0.00026 


0.00210 


-0.00048 


-0.00010 


-0.00115 


-0.00279 


-0.00130 


-0.00032 


-5.000 


-0 . 00028 


-0.00032 


. 00044 


-0 . 00048 


-0 . 00057 


-0 . 00089 


-0.00144 


-0.00103 


-0 . 00070 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00064 


. 00079 


0.00026 


. 00080 


0.00149 


0.00146 


0.00161 


0.00151 


0.00131 


10.000 


0.00141 


0.00185 


0.00122 


0.00197 


0.00376 


0.00348 


0.00340 


0.00360 


. 00226 


16.300 


0.00226 


0.00321 


0.00336 


0.00441 


0.00740 


0.00698 


0.00725 


. 00834 


0.00805 


22.500 


0.00295 


0.00456 


0.00648 


0.00811 


0.01170 


0.01181 


0.01494 


0.0I62S 


0.01691 



ENGir>£ER 
OATE ! 






FIGURE 4.1.1.2-49 

EFFECT OF BCOY FLAP 



4.1.1.2-53 



cr 



c- i .: .-> r 



CC-5C. i 



.M 



& 



fpj^ Rockwell International 

Space Division 



1 



MACH NUMBER 



3.000 



DELBF CDEG) 

-25 25 

| I I I ( 



GD 
< 
U 
Q 




CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR ¥0 " 8L 0.0 IN. 

MOMENT REFERENCE ZO - UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN 8W - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB - 1290-3 IN. 



DEL8F (CEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



ALPHA (CEG) 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
D 



10.000 

E 



15.000 

F 



800Y FLAP AXIAL FORCE INCREMENT 



-0.00009 
-0.00008 
.0 

.000 It 
.00035 
.00069 
.00113 



-0.00065 
-0.00029 
0.0 

0.00029 
0.00056 
0.00098 
0.00221 



-0.00119 
-0 . 00049 
0.0 

. 00044 
0.00081 
0.00136 
0.00267 



-0.00047 
-0.00037 
0.0 

0.00071 
0.00164 
0.00293 
. 00430 



-0.00083 
-0.00059 
0.0 

0.00102 
0.00240 
. 00440 
0.00661 



-0.00120 
-0.00084 
0.0 

0.00143 
0.00330 
0.00616 
0.00960 



ENGINEER iv^JL. 
DATE 3.r-t.l="?t 



FIGURE 4.1.1.2-50 

FFFF.CT OF BODY FLAP 



4.1.1.2-54 



20.000 
G 



-0.00141 
-0.00102 
0.0 

0.00163 
0.00401 
0.00763 
0.01176 



25.000 
H 



-0.00117 
-0.00113 
0.0 

0.00227 
0.00547 
0.01024 
0.01563 






€* 



Rockwell International 

Space Division 



MACH NUMBER 

■■"i I I I I I l I 



CD 

< 

u 
a 



.03 



.02 



.01 



.0 



-.oi l I i ' 



I 1 I I 



3.000 
l l l i I l 



DELBF CQEGD 

-25 25 

I I I I I 



I I 1 I 



1^,4. 




1 1 I .1 I I I I 



I I I I I I I I 



I I I 



1 i r 



i I ' i i i 



10 



15 



20 



25 30 35 

ALPHA CDEGD 



40 



45 



50 



CONFIGURATION 


BASELINE ORBITER VEHiaE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


CR YO « BL 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MOMENT REFERENCE: ZO - WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BCOY LENGTH LB = 1290.3 IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 






BCOY FLAP AXIAL FORCE 


INCREMENT 






-11.700 


-0.00120 


-0.0014-1 


-0.00117 


-0.00151 


-0.00090 


0.00025 


0.00141 


-5.000 


-0.0009H 


-0.00102 


-0.00113 


-0.00138 


-0.00127 


-0.00091 


-0.00050 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00143 


0.00163 


0.00227 


0.00318 


0.00410 


0.00421 


0.00357 


10.000 


0.00330 


0.00401 


0.00547 


,00708 


0.00824 


. 00849 


. 00853 


16.300 


0.00616 


. 00763 


0.01024 


0.01215 


0.01335 


0.01350 


0.01308 


22.500 


. 00960 


0.01176 


0.01553 


0.01729 


0.01830 


0.01305 


0.01485 



ENGINEER ^^2= 
DATE :_5_-AL-"^ 



FIGURE 4.1.1.2-51 

EFFECT OF BODY FLAP 



4.1.1.2-55 



ST 71 -.SH-GCGG iM 



fgl 



Rockwell International 

Spac* Division 



MACH NUMBER 



4.000 



DELBF CDEGD 

25 25 

[■ I I I I | I I I i 



< 
(J 
O 




5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORSITER VEHICLE 

CENTER Cf GRAVITY XO - FS 1075.7 IN. 

CR YO « BL 0.0 IN. 

MOMENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2590.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BODY LENGTH LB ■ 1290.3 IN. 



OELBF (0EG) 








ALPHA 


(DEG) 








-10.000 
A 


-5.000 
B 


0.0 

c 


5.000 
D 


10.000 

E 


15.000 

F 


20.000 
G 


25.000 

- H 






BODY 


FLAP AXIAL 


FORCE INCRE 


*£NT 






-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 


0.0 

0.0 

0.0 

0.00001 

0.00003 

0.00005 

0.0 


0.0 

0.00003 

0.0 
-0.00010 
-0.00026 
-0.00038 
-0.00008 


0.0 
-0.00002 
0.0 

0.00004 
0.00010 
. 00030 
. 00090 


-0.00002 
-O.OOOIS 
0.0 

. 00058 
0.00135 
0.00215 
0.00271 


-0.00010 
-0.00031 
0.0 

O.OOIOH 
0.00240 
0.00380 
. 00473 


0.0 
-0.00036 
0.0 

0.00149 
0.00310 
0.00484 
0.00625 


0.00008 
-0.00039 
0.0 

0.00147 
0.00330 
0.00562 
0.00791 


-0.00031 
-0.00075 
0.0 

0.00247 
0.00526 
0.00883 
0.01241 



ENGINEER ^i^J- 
OATE _Z.ft.*>J:18 



FIGURE 4.1.1.2-52 

EFFECT OF BODY FLAP 



%r/ 



4.1.1.2-56 



FL72-SH-0C60 IM 



€> 



Rockwell International 

Space Division 



MACH NUMBER 
•<*| I l l i I I i I i 



DELBF CDEGD 

-35 25 



CD 

< 
u 

Q 




25 30 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORB ITER VEHICLE 

CENTER OF GRAVITY XO » FS 1076.7 IN. 

OR YO = BL 0.0 IN. 

MOENT REFERENCE ZO = WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SUI = 2590.00 SQ.FT. 
WING SPAN BW = 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 





ALPHA 10EG1 




15.000 


20 . 000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


CELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 






BODY FLAP AXIAL FORCE 


INCPETENT 






-11.700 


0.0 


0.00008 


-0.00031 


-0.00091 


-0.00128 


-0.00164 


-0.00216 


-5.000 


-0.00036 


-0.00039 


-0.00075 


-0.00108 


-0.00137 


-0.00165 


-0.00199 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00149 


0.00147 


0.00247 


. 00309 


0.00331 


0.00357 


0.00410 


10.000 


0.00310 


. 00330 


0.00526 


0.00615 


0.00704 


0.00799 


0.00933 


16.300 


. 00484 


0.00562 


0.00883 


. 1 066 


0.01290 


0.01515 


0.01750 


22.500 


0.00625 


0.00791 


0.01241 


. 1 60 1 


0.02054 


0.02497 


0.02887 



ENGINEER "W^T- 
DATE Z3r3^L-^8 



FIGURE 4.1.1.2-53 

EFFECT OF BOQY FLAP 



4.1.1.2-57 



41 



Rockwell International 

Spaca Division 



MACH 



NUMBER 
ill! 



5.000 



DELBF CDEGD 

-25 25 

| I I I.I | I I I I t 



u. 

CO 

< 




-.01 



5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELIhE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1078.7 IN. 

or Yo « a. 0.0 IN. 

MOMENT REFERENCE ZO - ML 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2630.00 SQ.FT. 
WING SPAN 8W - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB " 1290.3 IN. 



DELBF . (DEO) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



ALPHA (DEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H 



BCOY FLAP AXIAL FORCE INCREMENT 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.00001 
0.00005 
0.0 
-0.00018 
-O.0OOH5 
-0.00070 
-0.00080 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



-0.00002 
-0.00015 
0.0 

0.00O+8 
0.00122 
0.00188 
0.00180 



-0.00009 
-0.00029 
0.0 

0.00092 
0.00227 
0.00352 
0.00391 



0; 00003 
-0.00032 
0.0 

0.00130 
0.00288 
0.0OM5O 
0.00566 



0.00017 
-0.00033 
0.0 

0.00121 
0.00290 
0.00521 

0.00765 



0.00021 
-0.00055 
0.0 

0.00237 
0.00502 
. OOEHH 
0.01193 



ENGINEER_L» W 2- 

oate ZAr-ferl* 



FIGURE 4.1.1.2-54 

EFFECT OF .BODY FLAP 



4.1.1.2-58 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 
■ ot +i l l 1 l 



DELBF CDEG) 

25 25 



00 

< 

a 
a 




-.01 



30 35 

ALPHA CDEG 3 









COWIGURATI 


BASEL INE 0RBITER 


VEHICLE 






CENTER OF GRAVITY 


XO 


- FS 


1076 


7 


IN. 


OR 


YO 


= BL 








IN. 


MOMENT REFERENCE 


zo 


= WL 


375 





IN. 



REFERENCE 0!f-£NSI0NS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW * 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB ■ 1290.3 IN. 





, 






ALPHA 


(OEG) 








15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50 . 000 


DELBF (OEG) 


F 


G 


H 


I 


J 


X 


L 


M 






BOOY 


FLAP AXIAL 


FORCE INCRE 


*€NT 






-11.700 


. 00003 


0.00017 


0.00021 


0.00003 


-0 . 00062 


-0.00140 


-0.00198 


-0.00221 


-5.000 


-0.00032 


-0.00033 


-0.00055 


-0.00074 


-0.00113 


-0.00155 


-0.00192 


-0 . 00220 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00130 


0.00121 


0.00237 


0.00307 


0.00294 


0.00321 


0.00403 


. 00500 


10.000 


0.00288 


0.00290 


. 00502 


0.00591 


0.00659 


. 00750 


0.00928 


0.01126 


16.300 


. 00450 


0.00521 


0. 00844 


0.01028 


0.01258 


0.01488 


0.017M3 


0.02014 


22.500 


0.00566 


0.00765 


0.0! 193 


0.01588 


0.02062 


0.02522 


. 02907 


0.03255 



ENGINEER 0U<*"Z- 

oate ZZ^r.i\r^l 



FIGURE 4.1.1.2-55 

FFFECT UF BODY FLAP 



4.1.1.2-59 



ri 72 



■ccec im 



#1* 



Rockwell International 
Space Division 



MACH NUMBER 

• w l I I M I I I I 



m 

< 



.03 



.08 



.01 



.0 



-.01 



8.000 

I I I I I I 



DELBF (DEO 

-25 25 

I I I i I I I I I I I 



1 I I I I I I I I I !' I I I I I I I 



-15 




-10 



5 10 

ALPHA CDEG3 



15 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DlhENSIONS 




CENTER Cf GRAVITY XO - FS 1075.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE 20 - UL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB - 1390.3 


IN. 



OELBF (PEG) 



-11.700 
-5.000 
0.0 
5.000 
10.000 
16.300 
32.500 



ALPHA (PEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



30.000 
G 



BCOY FLAP AXIAL FORCE INCREMENT 



-0.00005 
-0.00001 

0.0 
-0.00004 
-0.00013 
-0.00030 
-0.00013 



-0.00033 
-0.00003 

0.0 
-0.00031 
-0.00054 
-0.00083 
-0.00093 



-0.00030 
-0.00008 

0.0 
-0.00003 
-0.00014 
-0.00030 
-0.00010 



-0.00033 
-0.00017 
0.0 

0.00037 
0.00080 
0.00138 
0.00181 



-0.00004 
-0 . 00033 
0.0 

0.00083 
0.00171 
0.00378 
0.00403 



0.00003 
-0.00037 
0.0 

0.00116 
0.00321 
0.00373 
0.00559 



0.00003 
-0.00033 
0.0 

0.00101 
0.00243 
0.00463 
0.00739 



35.000 
H 



-0.00029 
-0.00066 
0.0 

0.00176 
0.00409 
0.00764 
0.01182 



ENGINEER 
DATE 



NEER to*l3» 



FIGURE 4.1.1.2-56 

EFFECT OF BODY FLAP 



4.1.1.2-60 



EC72-SH-CC60 1M 



4* 



Rockwell International 

Space Division 



MACH NUMBER 
•<* ■ MM 



8.000 



DELBF CDEG) 

-25 



25 



co 
< 
u 

Q 



.03 



.02 



.01 



-.01 



-J=— p> 



-L_L 



I I I 



■i i i r 



i i . i i. 



TM I I 



Mil 



i I I 




i I I I 



III! 



ti i ~r 



i i i 



II I! 



J_L_L 



II I I 



I I I l 



10 



15 



20 



25 



30 
ALPHA 



35 

CDEGD 



40 



45 



50 



J_LJ 
55 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE OlfENSIONS 


CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW = 2590.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


M>ENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW • 39.560 FT. 




BODY LENGTH LB » 1290.3 IN. 





' ' 






ALPHA 


(DEG) 








15.000 


20 . 000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50.000 


DELBF CDEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BOOY 


FLAP AXIAL 


FORCE INCRE 


"■ENT 






. -11.700 


0.00003 


. 00002 


-0.00029 


-0.00076 


-0.00099 


-0.00123 


-0.00160 


-0.00183 


-5.000 


-0 . 00027 


-0 . 00033 


-0.00055 


-0.00096 


-0-00123 


-0.00150 


-0.00182 


-0.00211 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00116 


0.00101 


0.00176 


0.00233 


. 00303 


0.00380 


0.00482 


0.00582 


10.000 


0.00221 


. 00242 


0.00409 


0.00511 


. 00660 


0.00819 


0.01024 


0. 01187 


15.300 


0.00373 


0.00462 


0.00764 


0.00963 


0.01229 


0.01501 


0.01768 


. 02056 


22.500 


0.00559 


. 00729 


0.01 182 


0.01546 


0.02005 


0.02487 


0.02911 


. 03346 



ENGINEER k>»*1. 
DATE "fLzjLL-ll 



FIGURE 4.1.1.2-57 

EFFECT OF BODY FLAP 



4.1.1.2-61 



LI 7--l.H-Ci.6C 1M 



li- 
< 

8 



jjji% Rockwell International 

Space OMaian 



I 



MACH NUMBER = 10.000 

■0t| I M I I i I I I I I'l I "TIT 



DELBF CDEG) 
-as o as 

i i i i I i i i i 




I i i i I I i i i I i i i i I t i i t I i i i i I I i i 

5 10 15 30 25 

ALPHA CDEGD " 



CCNF IGLRATION 



BASELirC 0RBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

CR YO - BL 0.0 IN. 

MO-ENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW « 2690.00 SQ.FT. 
WING SPAN BW « 7e,056 FT. 
M.A.C. CW - 39.560 FT. 
BCOY LENGTH LB - ia90.3 IN, 









1 — 


ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP AXIAL 


FORCE 1NCRE 


'■ENT 




... 


-11 .700 


0.0 


0.00001 


0.0 


-0.00005 


-0.00017 


-0.0002H 


-0.00027 


-0 . 0004H 


-5.000 


0.0 


0.00005 


0.0 


-0.00010 


-0 . 00023 


-0.00031 


-0.00039 


-0.00065 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00013 


0.0 


0.00025 


0.000H9 


0.00063 


0.00073 


0.00112 


10.000 


0.0 


-0.00030 


0.0 


0.00060 


0.00118 


0.00152 


0.00191 


0.00332 


16.300 


0.0 


-0.00055 


0.0 


0.00117 


0.00239 


0.00317 


O.O0HO2 


0.00692 


22.500. 


0.0 


-0.00080 


0.0 


0.00197 


O.0OH17 


0.00546 


0.00671 


0.01122 



ENG INt£H_ _1*JMJ~ 

oate ■I5»3j-'?y 



FIGURE 4.1.1.2-58- 

FFFFCT OF BG0Y FLAP 



4.1.1.2-62 



sr 



72-SH-CC60 1M 



\s 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



10. 000 
I I i i i l 



DELBF COEGD 

-25 25 



1 



CD 
< 

U 

Q 




30 35 
ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO * FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOt-£NT REFERENCE ZO = U. 375.0 IN. 



REFERENCE Dir-ENSICNS 
WING AREA SW = 25S0.00 SO. FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BCOY LENGTH LB =■ 1590.3 IN. 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


DELBF <OEG> 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP AXIAL 


FORCE INCRE 


'-ENT 






-11.700 


-0.0002'+ 


-0.00027 


-0.00044 


-0 . 00064 


-0.00056 


-0.00058 


-0.00105 


-0.00151 


-5.000 


-0.00031 


-0.00038 


-0.00065 


-0.00091 


-0. 001 10 


-0.00128 


-0.00161 


-0.00198 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00063 


0.00073 


0.00112 


0.00179 


0.00269 


0.00354 


. 00462 


0.00575 


10.000 


0.00152 


0.00191 


0.00332 


. 00488 


0.00632 


0.00781 


0.00991 


0-01 171 


16.300 


0.00317 


. 00402 


0.00692 


0.00954 


0.01211 


0.01453 


0.01720 


0.02040 


22.500 


0.00546 


0.0C671 


0.01122 


0.01483 


0.01931 


0.02420 


0.02876 


. 03377 



ENGINEER \Mf^2- 
DATE jfj?JkL-l% 



FIGURE 4.1.1.2-59 
EFFECT GF BODY FLAP 



4.1.1.2-63 



L :2"Jr-:-CC6C im 



'i* 



Rockwell International 

Space Division 

I 



MACH NUMBER = 15.000 

• 04 i l I I I I I I i i I i i i i I i i i i i i 



DELBF CDEG) 

-25 25 



It- 
CD 

< 



.03 



.02 



.01 



.01 



■A A 



I i I 



\-A- 



'III 



i» i Di» i O i flfl B ■ Qg gj^ sg ^ kOfre Oy 



I I I I 



■ I I I 



I i I I ' i'l I I I I I 




I I I I 



J_ 



I I 1 



I I I I 



•15 



-10 



5 
ALPHA 



10 

CDEG3 



15 



20 



25 



30 



CONFIGURATION 




BASELINE CR8ITER VEHICLE 


REFERENCE OlfEhSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU - 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.055 


FT. 


MOtENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 33.550 


FT. 




BODY LENGTH L8 » 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






800Y 


FLAP AXIAL 


FORCE INCREI 


hENT 






-11.700 


0.0 


0.00001 


0.0 


-0.00005 


-0.00017 


-0.00024 


-0.00027 


-0.00044 


-5.000 


0.0 


0.00005 


0.0 


-0.00010 


-0.00023 


-0.00031 


-0.00038 


-0.00065 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00013 


0.0 


0.00025 


O.0OOH9 


0.00063 


0.00073 


0.00112 


10.000 


0.0 


-0.00030 


0.0 


0.00060 


0.00118 


0.00152 


0.00191 


0.00332 


16.300 


0.0 


-0.00055 


0.0 


0.00117 


0.00239 


0.00317 


0.00402 


0.00692 


22.500 


0.0 


-0 . 00080 


0.0 


0.00197 


0.00417 


. 0C546 


0.00671 


0.01122 



ENGINEER_to^3 ! . 
DATE _.j.lU-J8 



FIGURE 4.1.1.2-60 

EFFECT OF BODY FLAP 



s~s 



4.1.1.2-64 



:m.o 



i ;v< 



#1* 



Rockwell International 

Space Division 



MACH NUMBER 



15.000 



OELBF CDEG) 
-as 25 



LL 

CD 

< 

a 




CONFIGURATION 



BASELINE CR81TER VEHICLE 

CENTER OF GRAVITY XO * FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOENT REFERENCE ZO * UL 375.0 IN. 



REFERENCE Dir-CNSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.055 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



OELBF (PEG) 



-11.700 
-5.000 

0.0 

5. COO 
10.000 
16.300 
22.500 



ALPHA (OEG) 



15.000 

F 



20.000 
G 



25.000 
H 



30.000 
I 



35.000 
J 



HO . 000 
X 



45.000 

L 



50.000 
M 



BODY FLAP AXIAL FORCE INCRE^NT 



-0.00024 
-0.00031 
0.0 

. 00063 
0.00152 
0.00317 
. 00546 



-0.00027 
-0.00038 
0.0 

0.00073 
0.00191 
. 00402 
0.0Q57I 



-0.00044 
-0 . 00065 
0.0 

0.00112 
0.00332 
0.00692 
. 1 1 22 



-0 . 00064 
-0.00091 
0.0 

0.00179 
G.C0488 
0.00954 
0.01483 



-0.00066 
-0.00110 
0.0 

. 00269 
0.00632 
0.01211 
0.01931 



-0.00068 
-0.00128 
0.0 

0.00354 
0.00781 
0.01453 
. 02420 



-0.C0105 
-0.00161 
0.0 

0.00452 
0.00991 
0.01720 
. 02876 



-0.00151 
-0.00198 
0.0 

. 00575 
0.01 171 
0.02040 
0.03377 



ENGINEER (A^SJS- 
DATE ZZ-lxll'IS 



FIGURE 4.1.1.2-61 

FFFECT OF BOOY FLAP 



4.1.1.2-65 



C l £ C I M 



'i* 



Rockwell International 
Space Division 

L 



MACH NUMBER = 20.000 

.OH 



.03 



DELBF CDEG) 

-25 25 

I'l ! I i I i I I'M 



< 

a 



.oa 



.01 



.01 
-15 



1 


1 1 1 


'I 1 1 1 


MM' 


'III! 


1 II 1 


MM 


MM 1 II i 1 t 


Mil 


_ 


















- 


- 


















- 




















— 


















. - 


_ 


















- 


_ 


















- 


- 


















— 


_ 


















- 


— 


















- 


— 




















- 








r^&^M 






-—~~~~~f^ 


^•7. 


- 






»-#"Su^Sg* 












- 


~l 


J 1 1 


Jill. 


MM 


MM 


_..l, 11 .!... 


MM 


1 I I I 


MM 


mm" 



■10 



5 

ALPHA 



10 

CDEGD 



15 



20 



25 



30 



CONFIGURATION 



BASELINE 0R81TER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO - BU 0.0 IN. 

MOENT REFERENCE 20 » H. 375.0 IN. 



REFERENCE D1^£NSI0NS 
WING AREA SW ' 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW • 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (CEG) 


A 


B 


c 





E 


F 


G 


H 






BCOY FLAP AXIAL FORCE INCREMENT 






-11.700 


0.0 


0.00001 


0.0 


-0.00005 


-0.00017 


-0.00024 


-0.00027 


-0.00044 


-5.000 


0.0 


0.00005 


0.0 


-0.00010 


-0.00023 


-0.00031 


-0.00038 


-0.00065 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00013 


0.0 


. 00025 


0.00049 


0.00063 


. 00073 


0.00112 


10.000 


0.0 


-0.00030 


0.0 


. 00060 


0.00118 


0.00152 


0.00191 


0.00332 


16.300 


0.0 


-0.00055 


0.0 


0.00117 


. 00239 


0.00317 


0.00402 


0.00592 


22.500 


0.0 


-0.00080 


0.0 


0.00197 


0.00417 


0.00546 


0.00671 


0.01122 



ENGINEER UA^Z- 
DATE St-UzI* 



FIGURE 4.1.1.2-62 

EFFECT OF BODY FLAP 



4.1.1.2-66 



c r t 



L72-SH-0CGC 1M 



ijjl 



Rockwell International 
Space Division 



MACH NUMBER 



20.000 



lo- 
rn 

< 



.04 



.03 



.02 



.01 



-.01 



DELBF CDEGD 
-25 25 

I i i i i | i i i ; 



ii r 



Hs-P- 



I I I 



I I I ~ I 







i i I r 



iii i r i i i 



i i i 




^^^~*^e4==~*cV 



i i i i 



J_L 



ll-li 



10 15 20 25 30 35 

ALPHA COEGD 



HO 



45 



50 



55 











CONFIGURATION 












BASEL INE ORBITER 


VEHICLE 






REFERENCE 


DI.^ENSIONS 






CENTER 


OF GRAVITY 


XO 


= FS 


1076 


7 


IN. 


WING 


AREA 


SW = 


2690 . 00 


SO.. 


FT. 




OR 


YO 


=■ BL 








IN. 


MING 


SPAN 


6W » 


78.055 


FT. 




MOMENT 


REFERENCE 


ZO 


- 14. 


375 





IN. 


M.A.C. 


CW = 


33.560 


FT. 


















BCOY 


LENGTH 


LB = 


1290.3 


IN. 













ALPHA 


(DEO) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELBF (0EG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP AXIAL 


FORCE INCREI 


^NT 






-11.700 


-0.00024 


-0.00027 


-0.00044 


-0.00064 


-0 . 00066 


-0.00068 


-0.00105 


-0.00151 


-5.000 


-0.00031 


-0.00038 


-0.00065 


-0.00091 


-0.00110 


-0.00128 


-0.0016! 


-0.00198 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00063 


0.00073 


0.00112 


0.00179 


0.00269 


. 00354 


. 00462 


. 00576 


10.000 


0.00152 


0.00191 


0.00332 


0.00488 


0.00632 


0.00781 


0.00991 


0.01171 


16.300 


0.00317 


0.00402 


. 00692 


0.00954 


'0.01211 


0.01453 


0.01720 


. 02040 


22.500 


0.00546 


0.00671 


0.01122 


0.01483 


0.01931 


0.02420 


. 02876 


. 03377 



ENGINEER 
DATE " 






FIGURE 4.1.1.2-63 

EFFECT OF BODY FLAP 



4.1.1.2-67 



Zl 



<2-:-iH-CCC C 



M 



4* 



Rockwell International 
Space DMston 



VBAR 
•P* t l l I l 



0. 005 through 0.080 

I I I I i 



DELBF CDEGJ 

-25 25 



CD 

< 




30 35 HO 

ALPHA (DEGD 



BASELINE ORBITER VEHICLE 
CENTER Cf" GRAVITY XO - FS 1076.7 
OR YO - BL 0.0 

MOfCNT REFERENCE 70 - W- 775.0 



GURA 


TION 






REFERENCE Dit-ENSICNS 




IN. 


WING AREA SW " 2690.00 


SQ.FT. 


IN. 


WING SPAN BW « 78.056 


FT. 


IN. 


M.A.C. CW - 39.560 


FT. 




8COY LENGTH LB - 1290.3 


IN. 





ALPHA !CEG) 






20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


0EL8F (DEG) 


A 


B 


C 


D 


E 


F 


G 






BCOY FLAP AXIAL FORCE 


INCREI-ENT 






-11.700 


-0.00027 


-0.00044 


-0.00064 


-0.00066 


-0.00068 


-0.00105 


-0.00151 


-5.000 


-0.00038 


-0.00065 


-0.00091 


-0.00110 


-0.00128 


-0.00161 


-0.00198 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00073 


0.00112 


0.00179 


0.00269 


0.00354 


0.00462 


0.00576 


10.000 


0.001S1 


0.00332 


0.00488 


0.00632 


0.00781 


0.00991 


0.01171 


16.300 


0.00402 


0.00692 


0.00954 


0.01211 


0.01453 


0.01720 


0.0204O 


22.500 


0.00671 


0.01122 


0.01483 


0.01931 


. 02420 


0.02876 


0.03377 



ENGINEER 
DATE 



FIGURE 4.1.1.2-64 

FFFFCT OF BODY FLAP 



4.1.1.2-68 



fE72-SH-CC€0 1M 



'i* 



Rockwell International 

Space Division 



ALTITUDE CFT. 3 = 300,000 to 600, 00C 

■ w i i i i i I i m i | i i i i i ri i i i i i i i 



DELBF CDEGD 
as 25 

rrrTT' i i i "t 



il- 
ea 

< 

8 




ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF" GRAVITY XO = FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MCtCNT REFERENCE ZO = U. 375.0 IN. 



REFERENCE OirENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW ■ 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 




20 . 000 


25.000 


30.000 


35.000 


40 . 000 


45.000 


50 . 000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 






BCOY FLAP AXIAL FORCE 


INCREt-ENT 






-11.700 


-0.00027 


-0.00044 


-0.00064 


-0.00066 


-0 . 00068 


-0.00105 


-0.00151 


-5.000 


-0.00038 


-0.00065 


-0.00091 


-0.00110 


-0.0012S 


-0.00161 


-0.00198 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00073 


0.00112 


0.00179 


0.00269 


0.00354 


0.00462 


. 00576 


10.000 


0.00191 


0.00332 


0.00488 


0.00632 


0.00781 


0.00991 


0.01171 


16.300 


0.00402 


0.00692 


0.00954 


0.01211 


0.01453 


0.01720 


0.02040 


22.500 


0.00671 


0.01122 


0.01483 


0.01931 


. 02420 


0.02976 


0.03377 



ENGINEER 
DATE 



FIGURE - 4.1.1.2-65 

EFFECT OF BCOY FLAP 



4.1.1.2-69 



£ L 



SH-CCCC 



i'Vi 



#J> 



Rockwell International 

Spec* Division 



MACH NUMBER 
•08, i | , | | | | i | I i 



DELSB CDEG) 

50 100 

I I I I I I I 



00 

to 

< 




CONFIGURATION 



BASELINE CRBITER VEHICLE REFERENCE DIMENSIONS 

CENTER OF GRAVITY XO - FS 1076.7 IN. WING AREA SW - 2690.00 SQ.FT. 

CR YO - 9- 0.0 IN. WING SPAN BW - 78.056 FT. 

MCt-tNT REFERENCE ZO - WL 375.0 IN. M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB - 1590.3 IN. 



DELSB (PEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (DEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H 



SPEEDBRAKE AXIAL FORCE INCR 



-0.01009 
-0.00620 
0.0 

0.00718 
0.01401 
0.02184 
0.03448 
0.05123 



-0.00923 
-0.00550 
0.0 

0.00720 
0.01388 
0.02172 
0.03407 
0.05055 



-0.00870 
-0.00500 
.0 

.00700 
.01330 
.02100 
.03340 



0.04960 



-0.00809 
-0.00483 
0.0 

0.00646 
0.01203 
0.01930 
0.03191 
0.0478H 



-0.00730 
-0.00463 
0.0 

0.00597 
0.01C88 
0.01775 
0.03046 
. 04S59 



-0.00659 
-0.00442 
0.0 

0.00590 
0.01098 
0.01703 
0.02942 
0.04614 



-0.00593 
-0.00419 
0.0 

0.0C581 
0.01113 
0.01688 
0.02893 
0.04616 



-0.00634 
-0.00296 
0.0 

0.00558 
0.01099 
0.01757 
0.03003 
0.04585 



ENGIf£ER_v£jI> 
DATE„LQ~^=2S> 



FIGURE 4.1.1.2- 66 

FFPFHT flF SPEEDBRAKE 



4.1.1.2-70 



SD72-SH-OC6C 1 M 



#1% 



Rockwell International 

Space Division 



_L 



MACH NUMBER 
• 08 r I I i i I i I I 



0.400 



DELSB CDEG) 

50 100 



00 

tn 
< 

u 

D 



1~T 



Mil 



i i I r 



i i i 



i i i i | i i i 
i i i i — r~rr 












CCNFI 


GURA 


BASELINE 0R8ITER 


VEHICLE 




CENTER 


OF GRAVITY 


XO 


= FS 


1076.7 


IN. 




CR 


YO 


• BL 


0.0 


IN. 


t-Of-CNT 


REFERENCE 


zo 


- WL 


375.0 


IN. 



\TION 




REFERENCE 


Dlt-ENSIONS 


WING AREA 


SW » 2690.00 SQ.FT. 


WING SPAN 


BW = 78.056 FT. 


M.A.C. 


CW = 39.560 FT. 


BCOY LENGTH 


LB » 1290.3 IN. 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 10.000 


15.000 


20.000 


25.000 


OELSB (DEG) 


A 


B 


c 


O 


E 


F 


G 


H 






SPEE 


DBRAKE AXIAL FORCE I NCR. 






0.0 


-0.01009 


-0.00923 


-0 . 00370 


-0 . 00809 


-0 . 00730 


-0.00659 


-O . 00593 


-0.00634 


15.000 


-0.00620 


-0 . 00550 


-0 . 00500 


-0 . 00483 


-0.CC463 


-0.00442 


-0.00419 


-O.0C296 


25.000 


0.0 


0.0 


0.0 


0.0 


0.D 


0.0 


0.0 


0.0 


35.000 


0.00718 


0.00720 


0.00700 


. 00S46 


0.00597 


. 00590 


0.00581 


0.00553 


45.000 


0.01401 


0.01388 


0.01330 


0.01203 


. 1 088 


0.01098 


0.011 13 


0.01C99 


55.000 


0.02184 


0.02172 


0.02100 


0.01930 


0.01775 


0.01703 


0.01663 


. 1 757 


70.000 


0.03448 


0.03407 


0.03340 


0.C3191 


. 030 u 6 


0.02942 


0.02893 


0.03003 


1 87.200 


0.05123 


0.05055 


. 04960 


0.04784 


0.04669 


. 046 1 4 


0.04615 


0.04585 



ENGtNEER^£)£D 
0ATE_J£.--J--:!S 



FIGURE 4.1.1.2-67 

EFFECT OF SPEEDBRAKE 



4.1.1.2-71 






^ Rockwell Intematic m 
Spaca Division 



MACH NUMBER = 0.G00 

•o 8 ; i i i i I i i i i I I i 



DELSB CDEGD 

50 100 

Ml! I I I I I 

i i i I i i r i i i i i i 



CO 

en 

< 
u 

Q 




CONFIGLRATION 



BASELINE 0R8ITER CHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - SL 0.0 IN. 

MCfCNT REFERENCE ZO - W. 375.0 IN. 



REFERENCE DIMENSIONS 
WINS AREA SW - 2630.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB - 1590.3 IN. 



CELSB 



(PEG) 
0.0 
15.000 
25.000 
35.000 
W.OOO 
55.000 
70.000 
87.200 



ALPHA (OEG) 



•10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H . 



SPEEDBRAKE AXIAL FORCE INCR. 



0.00658 


-0.00728 


0.00362 


-0.00388 


0.0 


0.0 


0.00601 


0.00708 


0.01499 


0.01549 


0.02518 


0.02441 


0.03711 


0.03591 


0.04830 


0.04583 



-0.00806 
-0.00403 
0.0 

0.00811 
0.01614 
0.02402 
0.03528 
0.04417 



-0.00819 
-0.00404 
0.0 

0.00789 
0.01559 
0.02318 
0.03478 
0.04355 



-0.00679 
-0.00358 
0.0 

0.00772 
0.01530 
0.02273 
0.03482 
0.04472 



-0.00619 
-0.0037! 
0.0 

0.00761 
0.01474 
0.02168 
0.03252 
0.04289 



-0.00552 
-0.00391 
0.0 

0.00800 
0.01433 
0.02038 
0.03000 
0.04174 



-0.00479 
-0.00419 
0.0 

0.00770 
0.01418 
0.01887 
. 02733 
0.04135 



ENGINEER L,^ 

OATE_Jt53iX-l£Cr 



FIGURE 4.1.1.2-68 

EFFECT OF SPEEDBRAKE . 



4.1.1.2-72 



SD72-SH-0C6C 1M 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 



0.800 



DELSB CDEGD 

50 100 



GO 
CO 

< 
u 

Q 




CONFIGURATION 



BASELINE ORB ITER VEHICLE 

CENTER CF GRAVITY XO » FS 1075.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO » W. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - £690.00 SQ.FT. 
WING SPAN BU * 78.055 FT. 
M.A.C. CW - 39.550 FT. 

BODY LENGTH LB - 1590.3 IN. 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB <CEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEEDBRAKE AXIAL FORCE I NCR. 






0.0 


-0.00477 


-0.00572 


-0 . 00663 


-0.00656 


-0.00535 


-0 . 00579 


-0.0C521 


-0 . 00660 


15.000 


-0.00351 


-0.00349 


-0.00343 


-0.00319 


-0.002S2 


-0.00335 


-0 . 00376 


-0.00414 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00622 


0.00752 


0.00911 


0.01066 


0.00906 


. 00783 


0.00661 


. 00543 


45.000 


0.01482 


0.01615 


0.01772 


0.01893 


0.01698 


0.01521 


0.01345 


0.01175 


55.000 


0.02500 


. 02506 


0.02550 


0.02551 


0.02410 


. 02223 


. 02044 


0.01877 


70 . 000 


0.03665 


0.03596 


0.03516 


. 0350H 


0.03502 


0.03290 


0.03012 


0.02775 


87.200 


0.05278 


. 05024 


0.04746 


. 04654 


. C4509 


0.0^153 


0.03895 


0.03715 



ENGINEER ^*f£> 



FIGURE 4.1.1.2-69 

EFFECT QF SPEEDBRAKE 



4.1.1.2-73 



SD72-SH-CC6C iM 



§PA Rockwell International 



Spac* Division 



1 



MACH NUMBER = 0.900 

•08| | I I 1 I I I I I I I I I 



DELSB CDEG) 

50 100 



m 

(SI 

< 




CONFIGURATION 



8ASELIf>E ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOI-ENT REFERENCE 20 - WL 375.0 IN. 



REFERENCE OI^ENSI0^6 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB ■ 1290-3 IN. 



DELSB (OEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (OEG) 



■10.000 
A 



-5.000 
B 



0.0 

C 



5.000 




10.000 

E 



15.000 

F 



20 . 000 
G 



25.000 
H 



SPEEOBRAKE AXIAL FORCE INCR. 



-0.00239 
-0.00195 
0.0 

0.00550 
0.01408 
0.02423 
0.03826 
0.05338 



-0.00379 
-O.0027H 
0.0 

0.00741 
0.01585 
0.02467 
0.03710 
0.05084 



-0.00517 
-0.00351 
0.0 

0.00926 
0.01731 
0.02453 
0.03549 
' 0.04868 



-0.00463 
-0.00385 
0.0 

0.00928 
0.01799 
0.02574 
0.03584 
0.04729 



-0.00542 
-0.00242 
0.0 

0.00868 
0.01749 
0.02647 
0.03423 
0.04708 



-0.00549 
-0.00272 
0.0 

0.00769 
0.01566 
0.02391 
0.03304 
0.04433 



-0.00530 
-0.00291 
0.0 

0.00650 
0.01348 
0.02098 
0.03123 
0.04084 



-0.00485 
-0.00301 
0.0 

0.00514 
0.01102 
0.01779 
0.02887 
0.03673 



FIGURE 4.1.1.2-70 

FFFFC.T OF SPEED8RAKE 



4.1.1.2-71* 



SD72-SH-0C60 1M 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 
■° 8 ' lilt 



.06 



CQ 

< 
U 
Q 



.02 



1 I I. 



I I I I 



0.950 

I I l i 



DELSB CDEG) 

50 1 00 



J_L 




_L_L 



I I I 



J_i_JL_L 



I I I I I I I I I 



I I i 



I I I i 



=y==^ 



J I I I 



^2L 



j_j_ 



-I I I L 



■10 



to 
ALPHA 



15 

CDEGD 



20 



25 



30 



35 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE D It-ENSICNS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOt-tNT REFERENCE ZO - VL 375.0 IN. 


M.A.C. CW « 39.550 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA (DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB CDEG) 


A 


B 


C 


O 


E 


F 


G 


H 


SPEEDBRAKE AXIAL FORCE I NCR. 




0.0 


-0.00466 


-0.00511 


-0.00530 


-0 . 00573 


-0.00660 


-0.00701 


-0.00701 


-0 . 00655 


15.000 


-0 . 00383 


-0.00443 


-0 . 00400 


-0.00314 


-0.00370 


-0 . 00387 


-0 . 00372 


-0 . 00308 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00695 


0.00793 


0.00884 


0.00830 


0.00827 


0.0C6e9 


0.00532 


. C0357 


H5.000 


0.01493 


0.01541 


0.01576 


0.01519 


0.01633 


0.01367 


0.01062 


0.00729 


55.000 


0.02373 


0.02249 


0.02101 


. 02093 


. 02395 


0.02013 


0.01579 


0.01103 


70.000 


0.03406 


. 03307 


0.03178 


0.03210 


0.03394 


0.02935 


. 02378 


0.01741 


87.200 


. 05063 


0.04824 


. 04537 


0.04624 


0.04377 


0.03803 


. 03065 


0.02187 



ENGINEER xSST> 

oate ic"3;v 



FIGURE 4.1.1.2-71 

EFFECT OF SPEEDBRAKE 



4.1.1.2-75 



ift 



Rockwell International 
Space Division 



MACH 
TT1 



NUMBER 



DELSB CDEG) 

50 100 

I I IT 



CQ 

< 

u 

Q 




COflGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO « F5 1076.7 IN. 
OR YO - BL 0.0 IN. 

MOENT REFERENCE ZP - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW » 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BCOY I FNGTH LB " 1290.3 IN. 



CCLS8 (PEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (C€G> 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
O 



10. 000 
E 



15.000 

F 



20 . 000 
G 



25.000 
H 



SPEEC6RAKE AXIAL FORCE 1NCR. 



-0.0CN78 
-0.00H10 
0.0 

0.00777 
0.01506 
0.02458 
0.03468 
0.05112 



-0. 00495 
-0.00454 
0.0 

0.00826 
0.01591 
0.02303 
0.03358 
0.04840 



-0.00480 
-0.00394 
0.0 

0.00873 
0.01591 
0.02143 
0.03221 
0.04533 



-0.00547 
-0.00286 
0.0 

0.00814 
0.01516 
O.021O2 
0.03219 

0.045e4 



-0.00646 
-0.00383 
0.0 

0.00815 
0.01626 
0.02379 
0.03416 
. 04346 



-0.00690 
-0.00387 
0.0 

0.00691 
0.01377 
0.02016 
0.02939 
0.03752 



-0.00692 
-0.00378 
0.0 

0.00568 
0.01094 
0.01598 
0.02341 
0.02954 



-0.00646 
-0.00334 
0.0 

0.00384 
0.00782 
0.01132 
0.01658 
0.01991 



ENGINEER*^ 
DATE„LO--_'3_-da_ 



FIGURE 4.1.1.2-72 

FFFECT OF SPEEOBRAKE 



4.1.1.2-76 



£C72-SH-CCeO 1M 



'1* 



Rockwell International 

Space Division 



1.050 



MACH NUMBER 
• 08 ' I I l i I l i l i I i i i i I i i i i I i i i i 



m 

< 
(j 
Q 



OELSB CDEGD 

50 100 

1 I I I ! | I I I I | 



.02 
-10 



I 1 I I 



I 1 I I 



M il 



J_J_ 




i i ! I I I i I i I I I I I I i i 



J_L 



J..1 .1 



I I I I 



10 15 

ALPHA CDEGD 



20 



25 



30 



35 



CONFIGURATION 




8ASELIME 0R9ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN EW - 78.055 


FT. 


MOMENT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BODY LENGTH LB - 1290.3 


IN. 



ENGINEER 
DATE„JsH5_-."i5_ 



FIGURE 4.1.1.2-73 

EFFECT OF SPEEDBRAKE 





ALPHA (DEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEG) 


A 


S 


C 


O 


E 


F 


G 


H 






SPEE 


DBRAKE AXIAL FORCE INC 


R. 






0.0 


-0 . 00302 


-0.00254 


-0 . 0020 1 


-0 . 00267 


-0.00436 


-0.00487 


-0.00514 


-0.00515 


15.000 


-0 . 00353 


-0.00345 


-0.0O311 


-0 . 00269 


-0.00348 


-0 . 00360 


-0.00352 


-0 . 00349 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


. 00955 


0.00910 


. 00890 


. 00853 


0.00828 


0.00751 


0.00674 


. 00558 


45 . 000 


0.01940 


0.01905 


0.01860 


0.01813 


0.01754 


0.01650 


0.01497 


0.01311 


55.000 


0.02930 


0.02799 


. 02548 


0.02604 


0.02596 


0.02435 


0.02217 


0.01945 


70 . 000 


0.04158 


0.03934 


0.03685 


0.03602 


0.03625 


0.03400 


0.03039 


0.02575 


37.200 


0.05554 


0.05159 


0.047Q1 


. 04548 


0.04547 


0.04274 


0.03629 


0.02921 



4.1.1.2-77 



£'D72~RH~CCeC iM 



4* 



Rockwell International 
Spaca Division 



MACH NUMBER 



1.100 



DELSB CDEGD 

50 100 



00 

< 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO " 9- 0.0 IN. 

MGtCNT REFERENCE 20-14. 375.0 IN. 



REFERENCE DIfCNSI0N5 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.550 FT. 

BOOY LENGTH LB - 1590.3 IN. 





ALPHA (CEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (CEG) 


A 


B 


C 


O 


E 


F 


G 


H 






SPEE 


D6RAKE AXIAL FORCE INCI 


3. 




r———^— 


0.0 


-0.00263 


-0.00179 


-0.00091 


-0.00177 


-0.00371 


-0.00420 


-0.00450 


-0.00462 


15.000 


-0.00359 


-0 . 00322 


-0 . 0C284 


-0.00302 


-0.00347 


-0.00354 


-0.00350 


-0.00335 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.01006 


0.00943 


0.00878 


0.00844 


0.00813 


0.00785 


0.00742 


0.00683 


45.000 


0.02110 


0.02024 


0.01939 


0.01886 


0.01784 


0.01733 


0.01645 


0.01523 


55.000 


0.03102 


0.02970 


0.02836 


0.02758 


0.02637 


0.02553 


0.02407 


0.02201 


70.000 


0.04410 


0.04152 


0.03875 


0.03724 


0.03690 


0.03523 


0.03241 


0.02854 


87.200 


0.05710 


0.05260 


0.04756 


0.04493 


0.04680 


0.C43S3 


0.03897 


0.03235 



ENGINEER l3a£> 

DATE_i5»rI4r23_ 



FIGURE 4.1.1.2-74 

FFFFCT OF SPEED8PAKE 



\~/ 



4.1.1-2-78 



s;. ( 



'i* 



Rockwell International 

Spac* Division 



MACH NUMBER 
•° 9 ' I i l l 



1.200 



DELSB CDEGD 

50 



100 



CO 
CD 
< 
CJ 
Q 












CONFI 


GUR/ 


BASEL INE ORBITER 


VEHICLE 






CENTER 


CF GRAVITY 


XO 


« fs 


1076 


7 


IN. 




OR 


YO 


- a. 








IN. 


MOMENT 


REFERENCE 


ZO 


« M. 


375 





IN. 



DELS3 (OEGl 



0.0 
15. 000 
25.000 
35.000 
45 . 000 
55.000 
70.000 
87.200 



REFERENCE OlrENSICNS 
WING AREA SW - 2690.00 SO. FT. 
UING SPAN BUI ■ 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



ALPHA (PEG) 



-10.000 
A 



-0.00441 
-0.00506 
0.0 

0.00753 
0.01619 
0.02513 
0.03946 
0.05129 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



20 . 000 
G 



SPEEPaRAKE AXIAL FORCE I NCR. 



-0.00465 
-0 . 00444 
0.0 

0.00726 
0.01624 
0.02598 
0.03919 
. 04958 



-0 . 00467 
-0.00358 
0.0 

. 00563 
0.01580 
0.02625 
0.03822 
0.04705 



-0 . 00548 
-0.00491 
0.0 

0.00659 
0.01473 
. 02373 
0.03454 
0.04279 



-0.00513 
-0.00418 
0.0 

. 00529 
0.01415 
. 02290 
0.C3337 
0.0^031 



-0.00575 
-0.00371 
0.0 

0.00754 
0.01464 
0.02100 
0.02930 
0.03517 



-0 . 00522 
-0.00316 
0.0 

0.00855 
0.01461 
0.01849 
0.02447 
. 02907 



25.000 
H 



-0.00454 
-0.00256 
0.0 

0.00929 
0.01406 
0.01529 
0.01903 
0.02217 



ENGINEER 
DATE 






FIGURE 4.1.1.2-75 

EFFECT OF SPEEDBRAKE 



4.1.1.2-79 



r r 



4% 



Rockwell International 

SpacaDMsicn 



MACH NUMBER 
•08i | | | | | i i | i 



DELSB COEG) 

50 100 



CD 

< 




-.02 



10 15 

ALPHA CDEG) 



CONFIGURATION 



BASELINE CR8ITER \£HICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCfENT REFERENCE ZP - 14. 375.0 IN. 



REFERENCE Olf-ENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

eCOY LENGTH LB - 1290.3 IN. 



DELSB (DEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (DEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H 



SPFEraRAKE AXIAL FORCE INCR 



-0.00372 
-0.00613 
0.0 

0.00729 
0.01558 
0.02433 
0.03700 
0.04804 



-0.00488 
-0.00525 
0.0 

0.00704 
0.01562 
0.02493 
0.03772 
0.04849 



-0.00601 
-0.00429 
0.0 

0.00652 
0.01528 
0.02509 
0.03779 
0.04791 



-0.00600 
-0.00486 
0.0 

0.00634 
0.01428 
0.02309 
0.03512 
0.0452! 



-0.00575 
-0.00386 
0.0 

0.00591 
0.01302 
0.02095 
0.03255 
0,04069 



-0.00550 
-0.00348 
0.0 

0.00673 
0.01358 
0.02040 
0.02996 
0.03675 



-0.00529 
-0.00301 
0.0 

0.00743 
0.01387 
0.01926 
0.02688 
0.03205 



-0.00510 
-0.00253 
0.0 

0.00800 
0.01397 
0.01769 
0.02343 
0.02575 



ENGINEER., 
OATE_.Le>--4jil6- 



FIGURE 4.1.1.2-76 

EFFECTOFSPEEDPRAKE. 



V_x 



4.1.1.2-80 



SE72-SH-0C60 1 M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 
•° 8 ' l i i I 



1.500 



DELSB CDEGD 

50 100 

I I I I | I I I I { 



CO 
CO 

< 

a 
a 




CONFIGURATION 



BASELINE CRB1TER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCfENT REFERENCE ZO - W_ 375.0 IN. 



REFERENCE OlhENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB " 1390.3 IN. 



DELSB lOEG) 



0.0 
15.000 
35.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (DEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



20 . 000 
G 



SPEED8RAKE AXIAL FORCE I NCR. 



. 00277 


-0.00465 


. 00646 


-0 . 00549 


0.0 


0.0 


. 00663 


. 00648 


0.01416 


0.01422 


0.02241 


0.02266 


0.03378 


0.03482 


0.04491 


0.04639 



-0 . 00650 
-0 . 00452 
0.0 

0.00614 
0.01403 
0.02264 
0.03599 
. 04767 



-0 . 00592 
-0.C0443 
0.0 

0.00578 
0.01318 
0.02145 
. 03445 
. 04659 



-0.00493 
-0.00327 
0.0 

0.00521 
0.01129 
0.01827 
0.03057 
. 03S86 



-0 . 00490 
-0.00304 
0.0 

0.00532 
0.01189 
0.01902 
0.02945 
0.03741 



-0.00515 
-0 . 0029 1 
0.0 

0.00591 
0.01267 
0.01919 
0.02822 
0.03458 



25. COO 
H 



-0 . 00549 
-0.00259 
0.0 

. 006C5 
0.01295 
0.01944 
0.02713 
0.03144 



ENG!NE£9l£-».Z> 



FIGURE 4.1. 
EFF€CT 



1.2-77 

OF SPEEDBRAKE 



4.1.1.2-ai 



SD72-SH-CCCC ! .Yi 



Rockwell International 

Spacs Division 



MACH NUMBER 
.OSr-r-i-rr 



DELSB CDEGD 

50 100 

I I I I 



CD 

en 

< 
u 
a 




-.03 



ALPHA CDEGD 



CONFIGURATION 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MOt€NT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DII-ENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 











ALPHA (DEG) 










-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30.000 


DELS8 (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 


I 








SPEEDBRAK 


E AXIAL FORI 


:e inch. 








0.0 


-0.00215 


-0.00256 


-0.00295 


-0.00332 


-0.00304 


-0.00275 


-0.00275 


-0.00266 


-0.00250 


15.000 


-0.00236 


-0.00241 


-0.00243 


-0.00242 


-0.00222 


-0.00206 


-0.00233 


-0.00257 


-0.00277 


35.000 
35.000 


0.0 

0.00463 


0.0 
0.00449 


0.0 
0.00427 


0.0 
0.00400 


0.0 
0.00365 


0.0 
0.00333 


0.0 
0.00427 


0.0 
0.00517 


0.0 

0.00501 


45.000 


0.00982 


0.00973 


0.00948 


0.00906 


0.00844 


0.00843 


0.00905 


0.00959 


0.01 008 


55.000 


0.01594 


0.01584 


0.01547 


0.01487 


0.01415 


0.01445 


0.01411 


0.01371 


0.01328 


70.000 


0.02968 


0.02745 


0.02596 


0.02436 


0.02335 


0.02239 


0.02159 


0.02084 


. 020 1 7 


87.200 


0.04281 


0.04084 


0.03849 


0.03585 


0.03324 


0.03067 


0.02840 


0.02524 


. 02427 






ENGINEER 

DATE „1SL- 533- 



FIGURE 4.1.1.2-78 

PFFFCT OF SPEEDBRAKE 



4.1.1.2-82 



SD72-SH-0CGC 1M 



#1% 



Rockwell International 

Space Division 



MACH NUMEER 
• oe i M l I I I I I 



3.000 



DELSB CDEG) 

50 ! 00 

1 I i I i n i i r 



.06 



.04 



CQ 
(Si 

< 

u 
a 



.02 
-10 



J_L 



I I I I 



I I i I' I I 



I I I I 



I I I I 



ill! 




I I I I 



I I I I 



i i i I i i i i I i i i r 



i i 



i i i i 



1..L..1-L 



-5 



10 

ALPHA 



15 
CDEGD 



20 



25 



30 



35 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER CF GRAVITY XO » FS 1075.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W - 78.056 FT. 


MOTENT REFERENCE ZO - 14. 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BCOY LENGTH LB » 1290.3 IN. 











ALPHA (DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELS3 (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 


SPEEDBRAKE AXIAL FORCE I NCR. 


0.0 


-0.00610 


-O . 00592 


-0 . 00565 


-0 . 00529 


-0 . 00506 


-0.00481 


-0 . 004 1 7 


-0.00377 


15.000 


-0.00244 


-0.00237 


-0.00226 


-0.00212 


-0 . 00202 


-0.00193 


-0.00167 


-0.00151 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00167 


0.00175 


0.00179 


0.00178 


0.00176 


0.00171 


0.00146 


0.00140 


H5.000 


0.00727 


0.00560 


0.00587 


0.00509 


0.00466 


0.00439 


0.00397 


0.00321 


55.000 


0.01427 


0.01269 


0.01104 


. 00937 


0. 00841 


. 00772 


0.00691 


. 00552 


70.000 


0.02064 


0.01919 


0.01774 


0.01634 


0.01486 


0.01389 


0.01215 


0.01081 


87.200 


0.03148 


0.02957 


0.02773 


. 02604 


0.02380 


0.02185 


0.01954 


0.01743 



ENGINEER lJs^> 

DATE__i<£31"3I-r2>~ 



FIGURE 4.1.1.2-79 

EFFECT GF SPEEDBRAKE 



4.1.1.2-83 



|« Rockwell International 



Spac* Division 



MACH NUMBER = 3.000 

•08i | | | | I | | | | I I I I I j I I 



OELSB CDEGD 

50 100 

i i- i I i i r~r~ j 
i I i i i i I i i i i 



CD 

< 

u 

Q 




30 35 40 

ALPHA CDEG3 



COF1GURATI0N 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MCfCNT REFERENCE ZP - WL 375.0 IN. 



REFERENCE DlftNSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BCOY LENGTH LB - 1890.3 IN. 





ALPHA (DEG) 






15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 






SPEEDBRAKE AXIAL FORI 


CE 1NCR. 






0.0 


-0.00481 


-0.00417 


-0.00377 


-0.00317 


-0.00242 


-0.00153 


-0.00052 


15.000 


-0.00193 


-0.00167 


-0.00151 


-0.00127 


-0.00096 


-0.00061 


-0.00021 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00171 


0.001H6 


0.001H0 


0.00124 


0.00100 


. 00069 


0.00031 


45.000 


0.00439 


0.00397 


0.00321 


0.00237 


0.00208 


0.00150 


0.00110 


55.000 


0.00772 


0.00691 


0.00552 


0.00405 


0.00385 


0.00274 


0.00223 


70 . 000 


0.01389 


0.01215 


0.01081 


0.00924 


. 00747 


0.00556 


0.00354 


87.200 


0.02185 


0.01954 


0.01743 


0.01483 


0.01182 


0.00847 


0.00485 



ENGINEER.^^^ 
OATE LCL-Jrlg 



FIGURE 4.1.1.2-80 

FFFFHT OF SPEEDBRAKE 



4.1.1.2-84 



£D72-SH-0Cec I M 



'1* 



Rockwell International 
Space Division 



MACH NUMBER 



4.000 



DELSB CDEGD 

50 100 

I I i I | I i i I 1 
i I | , i i I" 



CD 
CO 

< 

u 
a 




CONF IGLRATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO • FS 1076.7 IN. 


WING AREA SU « 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZO » 14. 375.0 IN. 


H.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 





ALPHA (DEG) 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEG) 


A 


S 


c 


D 


E 


F 


G 


H 






SPEE 


DSRAKE AXIAL FORCE INC 


R. 






0.0 


-0.00177 


-0.00115 


-0 . 00070 


-0.00083 


-0.00095 


-0.001C6 


-0.00117 


-0.00127 


15.000 


-0.00071 


-0.00047 


-0 . 00030 


-0.00035 


-0.00040 


-0.00045 


-0.00049 


-0 . 00053 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00198 


0.00204 


0.00200 


0.00183 


0.001S5 


0.00145 


0.00125 


. 00083 


45.000 


0.00H55 


0.00425 


. 00390 


. 00349 


0.00302 


0.0C244 


0.00185 


0.00142 


55.000 


0.00842 


0.00739 


0.00650 


0.00588 


0.00518 


0.00417 


0.00313 


0.00257 


70 . 000 


0.01430 


0.01323 


0.01220 


0.01113 


0,00979 


0.00810 


0.00629 


. 00480 


87.200 


. 02349 


. 02200 


0.02050 


0.01874 


0.01661 


0.01438 


0.01189 


0.00803 



ENGINEER "^^ 
OATE.JOXE3S: 



FIGURE 4.1.1.2-81 

EFFECT OF SPEEDBRAKE 



4.1.1.2-85 



4* 



Rockwell International 

Space Division 



MACH NUMBER 
•W r- | l l I I I I I I 



4.000 



DELSB CDEG) 

50 100 



CD 

< 

8 




30 35 HO 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR YO - O. 0.0 IN. 

MOMENT REFERENCE ZP - WL 375.0 IN. 



REFERENCE 0ICCN5IONS 
WING AREA SW - 2690.00 SQ.FT. 
WINS SPAN BW " 78.056 FT. 
M.A.C. CW - 39.550 FT. 

BODY LENGTH LB - 1290.3 IN. 



DELSB (DEG) 


ALPHA (OEG) 






15.000 

F 


20.000 
G 


25.000 
H 


30 . 000 
I 


35.000 
J 


40.000 
K 


45.000 

L 






SPEEDBRAKE AXIAL FOR! 


CE I NCR. 






0.0 
t5.000 


-0.00106 
-0.00045 


-0. 00117 
-0.00049 


-0.00127 
-0 . 00053 


-0.00135 
-0.00056 


-0.00119 
-0.00053 


-0.00070 
-0.00042 


-0.00028 
-0.00032 


25.000 
35.000 


0.0 
0.00145 


0.0 
0.00125 


0.0 
0.00083 


0.0 
0.00083 


0.0 
0.00056 


0.0 
0.0 


0.0 
0.0 


45.000 
55.000 
70.000 
87.200 


0.00244 
0.00417 
0.00810 
0.0143B 


0.00185 
0.00313 
0.00629 
0.01189 


0.00142 
0.00257 
0.00460 
0.00803 


0.00145 
0.00190 
0.00325 
0.00521 


0.00098 
0.00111 
0.00178 
0.00329 


0.0 

0.00023 
0.00038 
. 00240 


0.0 
0.0 
0.0 
0.0 



ENGINEER_Ji&$, 

oate io£5rIS 



FIGURE 4.1.1.2-82 

EFFECT OF. SPEEDBRAKE 



4.1.1.2-86 



SE72-SH-OC6C 1M 



'1* 



Rockwell International 
Space Division 



MACH NUMBER 



DELS8 COEG) 

50 100 

I l l i I i I 



CD 

to 

< 










CONFI 


GUFU 


BASELY ORBITER 


VEHICLE 






CENTER OF GRAVITY 


XO 


« FS 


1076 


7 


IN. 


OR 


YO 


- BL 








IN. 


MCt-ENT REFERENCE 


ZC 


« WL 


375 





IN. 



0ELS8 (PEG) 



N 

REFERENCE DIMENSIONS 




WING AREA SW » 2690.00 


SQ.FT. 


WING SPAN BW = 78.056 


FT. 


M.A.C. CW - 39.560 


FT. 


BCOY LENGTH LB » 1 290- 3 


IN. 



-10.000 

A 



-5.000 
B 



0.0 


-0.00119 


-0.00158 


-0.00160 


15.000 


-0. 000*3 


-0.00058 


-0.00060 


25.000 


0.0 


0.0 


0.0 


35.000 


0.00144 


0.00152 


0.00150 


45.000 


0.00287 


0.00280 


0.00270 


55.000 


0.00625 


0.00543 


0.00470 


70.000 


0.01203 


0.01133 


0.01030 


87.200 


0.01978 


0.01729 


0.01580 



ALPHA (PEG) 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



SPEEDBRAKE AXIAL FORCE [NCR. 



-0.00089 
-0.00034 
0.0 

0.00131 
. 00253 
0.00408 
. 00877 
0.01425 



0.0 

0.0 

0.0 

0.00109 

0.00228 

. 00338 

0.00710 

0.01238 



0.0 
0.0 
0.0 

0.00085 
0.00188 
0.00257 
0.00562 
0.00995 



20.000 
G 



0.0 

0.0 

0.0 

0.00061 

0.00141 

0.00196 

0.00402 

0.00731 



25.000 
H 



0.0 

0.0 

0.0 

0.00040 

0.00071 

0.00133 

0.0021" 

. 00490 



ENGINEER ^f-0 

OATE.ji5.rI3-?rZs: 



FIGURE 4.1.1.2-83 

EFFECT OF SPEEDBRAKE. 



4.1.1.2-87 



i£ r< C C C: C < M 



I* 



sp>V& Rockwell International 

Space Division 

L 



MACH NUMBER 



en 

< 
u 
Q 



.08 



.06 



.OH 



.02 



-.02 



I I I 



,1111. 



I I I I I 



5.000 

Tl "I I I I I I I I I 



DELSB CDEG: 

50 100 

1 I I II I I I I I | 




I I 



I I I- I 



I I I I I I I 



! I I I i I i I 



•tfiO H S^l'.Z , 



15 



20 



30 



L_L I. I- I I I 

35 

ALPHA 



J.. I. I I 



i i i i 



J_1_L 



i I l I 



to 
CDEGD 



45 



,50 



55 



60 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER Of GRAVITY XO • FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MttCNT REFERENCE ZP - WL 375.0 IN. 



REFERENCE DI^£NSION5 
WING AREA SW - 2690. CO SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.550 FT. 

BODY LENGTH LB - 1290.3 IN. 





ALPHA (DEG) 






15.000 


20.000 


25.000 


30.000 


35.000 


HO. 000 


45.000 


50.000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 




' 


SPEEOBRAKE AXIAL FORCE [NCR. 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


■ 0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00085 


0.00061 


0.00040 


0.00010 


0.00006 


0.0 


0.0 


0.0 


15.000 


0.00188 


0.00141 


0.00071 


0.00015 


0.00006 


0.0 


0.0 


0.0 


55.000 


0.00267 


0.00196 


0.00133 


0.00015 


0.00005 


0.0 


0.0 


0.0 


70.000 


0.00562 


0.00402 


0.00217 


0.00050 


0.00029 


0.0. 


0.0 


0.0 


87.200 


0.00995 


0.00731 


0.00490 


0.0027! 


0.00123 


Q.P 


0.0 


0.0 



SSKggfe 



FIGURE 4.1.1.2-84 

EFFECT OF SPEEDBTAKE 



4.1.1.2-88 



SL72-SH-CCCC 1M 



* 



Rockwell International 
Spaca Division 



MACH NUMBER 



8. 000 



DELSB CDECO 

50 1 00 



CD 

< 

a 



.08 



.06 



.OH 



.03 



Tl IT 



I I I I I I 



I I 



I I I I I 




oaL-L-i 



I I I 



"1 TT~j i~~i TT~| 
I I I I i I I i 



CONFIGURATION 




BASELINE 0RB1TER VEHICLE 


REFERENCE Dlt-tNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU » 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCfENT REFERENCE ZP - WL 375.0 IN. 


M.A.C CW » 33.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


iDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (0EG) 


A 


5 


C 


D 


E 


F 


G . 


H 






SPEE 


DBRAKE AXIA 


L FORCE INC 


R. 






0.0 


-0.00177 


-0.00188 


-0.00130 


-0.00099 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00069 


-0 . 00073 


-0.00070 


-0.00038 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00090 


0.00032 


0.00070 


0.00053 


. 00046 


. 00023 


0.00010 


O.O0OC8 


45.000 


0.00191 


0.00163 


0.00140 


0.00121 


0.00093 


0.00062 


0.00024 


0.00017 


55.000 


0.00461 


0.00409 


0.00350 


0.00277 


0.00199 


0.00119 


0.00041 


. 00025 


70.000 


0.00932 


0.00S03 


. 00680 


0.00564 


0.00434 


0.00297 


0.00156 


. 00092 


87.200 


0.01538 


0.Q1409 


0.01210 


0.01056 


. 00876 


0.00510 


0.00325 


0.00192 



ENGINEER I^*D 
0ATE„"iOri2!ilD2> 



FIGURE 4.1.1.2-85 

EFFECT OF SPEEOBRAKE 



4.1.1.2-89 



SD72-SH-0CCC 



1M 






Rockwell International 

Sp«c*DMsion 



MACH NUMBER 



OELSB CDEG) 

50 100 

| I I I I | I I I I ) 



.08 



.06 



.OH 



CD 
CO 

< 

8 



l I I I I 




i I I I I I I I I I I 



g K7r7^th"iri~3 ryj~ usrn j<*x 



i I i 



i i i i 



_L_L 



t- W- LKL ' iKUl K.H - E S-*- 



I ' I I ' ' I I 1 



35 

ALPHA 



HO 
CDEGD 



H5 



50 



CONFIGURATION 



BASELINE 0R8ITER VEHICLE 
CENTER Cf GRAVITY XO - FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MO-CNT REFERENCE ZT> » WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW ■ 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB ■ 1590.3 IN. 



OELSB 



ENGINEER t&D 
OATE__JS£?r3I:!j* 



FIGURE 4.1.1.2-56 

FFFFf;T CF SPEEDBRAKE 



* — M M- 



55 



i I l l I 
60 











ALPHA 


(OEG) 










15.000 


20.000 


25.000 


30.000 


35.000 


HO. 000 


H5.000 


50 . 000 




F 


G 


H 


I 


J 


K 


L 


M 


1 (OEG! 






SPEE 


03RAKE AXIAI 


L FORCE INCI 


3. 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 
0.0 


35.000 


0.00028 


0.00010 


0.0C008 


0.0 


0.0 


0.0 


0.0 


H5.000 


0.00062 


0.0002H 


0.00017 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


0.00119 


0.00041 


0.00025 


0.00010 


0.00003 


0.0 


0.0 


0.0 


70.000 


0.00297 


0.00155 


0.00092 


0.00020 


0.00007 


0.0 


0.0 


0.0 


87.200 


0.00610 


0.00325 


0.00192 


0.00138 


. 00069 


0.0 


0.0 


0.0 



4.1.1.2-90 



SD72-SH-CCCC i M 



€> 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 
T~i i i I n - 1 i i i r 



DELSB CDEG: 

50 100 



CD 
if) 

< 

u 
o 




CONFIGURATION 



BASELINE 0R9ITER VEHICLE 
CENTER Cf GRAVITY XO « FS 1076. 7 IN. 
OR YO " SL 0.0 IN. 

MOMENT REFERENCE ZP - 14. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW « 2690.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CU - 39.560 FT. 

BODY LENGTH LB = 1390.3 IN. 





— ■— " 






ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEGl 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


DBRAKE AXIAI 


L FORCE INC 


R. 






0.0 


-0.00207 


-0.00221 


-0.00210 


-0.00114 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00079 


-O.OOOBH 


-0.00080 


-0.000H3 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


. 00055 


0.00063 


0.00063 


0.00054 


0.00041 


0.00031 


. 00024 


0.00018 


45.000 


0.00102 


0.00123 


0.00130 


0.00111 


. 00088 


0.00069 


0.00052 


0.00035 


55.000 


0.00254 


0.00289 


. 00300 


0.00276 


0.00229 


0.00155 


0.00079 


. 00053 


70.000 


0.00557 


0.00631 


0.00640 


0.00549 


0.00425 


. 00278 


0.00127 


. 000S2 


87.200 


0-01008 


0.01150 


0.01170 


0.01007 


. 00797 


. 00543 


0.00253 


0.00219 



ENGINEER ■ 

iDATE.iOr-C-ZTS 5 



FIGURE 4.1.1.2-87 

EFFECT OF SPEEDBRAKE 



4.1.1.2-91 



i. L 7 ^ - L ri • C C C C : M 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



DELSB CDEG} 

50 100 



| I I I I 



• 08 n | | | | | | | I [ I I I I | i'IT 



00 
CD 

< 



.06 



.OH 



.02 



.0 f> 



.03 



I I I I 



I. 1 1. 



J_JL 



l I I 



I I I I I I I 



TV! 'I" 



I > I I t 



r r v ^f^^^f^ri^T^^r-^-i 1 ^^ jrjn^c^Lnr^ ^ j ' we uu 



± 



15 



20 



i I 1 I I I I I 
HO 



1_,}' \ H W.H 



-L-L 



*— M — *- 



25 30 35 

ALPHA CDEGD 



H5 



50 

31 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - F5 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



55 



60 





U PHA (DEG) 






15.000 


20.000 


25.000 


30.000 


35.000 


HO. 000 


H5.000 


50.000 


DELSB (OEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEE 


DBRAKE AXIAL FORCE INC 


=!. 




- 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


o.o 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00031 


0.0002H 


0.00018 


0.0 


0.0 


0.0 


0.0 


0.0 


H5.000 


0.00069 


0.00052 


0.00035 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


0.00155 


0.00079 


0.00053 


0.00010 


0.00003 


0.0 


0.0 


0.0 


70.000 


0. 00278 


0.00127 


0.00092 


0.00020 


0.00007 


0.0 


0.0 


0.0 


87.200 


0.005H3 


0.002SB 


0.00219 


0.00138 


0.00068 


0.0 


0.0 


0.0 



ENGINEER 3&^L 

DATE__lg_-_5::T% 



FIGURE 4.1.1.2-38 

FFFFCT OF SPEEDBRAKE 



4.1.1.2-92 



6L72-SH-0C6C 



1M 



#1% 



Rockwell International 

Spaca Division 



MACH NUMBER 
• 08 | I I i ! I I i II I I 



15.000 



m 

(Si 

< 

CJ 

Q 



.06 



.OH 



.03 



I II I I I 




DELSB CDEG) 

50 1 00 

| I I I I | II I i } 

I I I i I I I I I !'l I I I I I I 



.02 



j_j_ 



J_1_J_JL 



_i_L 



l I I I 



I I I I 



J I I I. 



-10 



10 
ALPHA 



15 

CDEGD 



20 



25 



30 



35 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DlftNSIGNS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW • 78.056 


FT. 


MOMENT REFERENCE ZO - U_ 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25. COO 


CELS8 (DEG1 


A 


B 


C 


D 


E 


F 


G 


H 






SPEE 


D8RARTAXIA 


L FORCE INC 


R. 






0.0 


-0.00207 


-0.00221 


-0.00210 


-0.00114 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00079 


-0.00084 


-0.00080 


-0.00043 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00055 


0.00063 


0.00068 


0.00054 


0.00041 


0.00031 


0.00024 


0.00018 


45.000 


0.00102 


0.00123 


0.00130 


0.00111 


0.00088 


0.00069 


0.00052 


0.00035 


55.000 


0.00254 


0.00289 


0.00300 


. 00276 


0.00228 


0.00155 


0.00079 


0.00053 


70.000 


0.00557 


0.00631 


0.00640 


0.00549 


0.00425 


. 00278 


0.00127 


0.00092 


37.200 


.0 1 008 


0.01150 


0.01170 


0.01007 


0.00797 


0.00543 


0.00268 


0.00219 



ENGINEER J^£> 
OATE„iQl-_5;Iie 



FIGURE 4.1.1.2-89 

EFFECT OF SPEEDBRAKE 



4.1.1.2-93 



SD72-SH-CC£C iM 



$1% 



Rockwell International 
Space Division 



MACH NUMBER 



15.000 



DELSB CDEGD 

50 100 

P' I I I | I I I I 



CD 
CD 

< 

8 



.08 



.06 



.04 



.02 



TT 



i r - rF& 



.02 



TT 



I I I I 



^^S ! ^i^^^ - i » L l^-rT l ~ r >^-jA-iri';ar'^ l fe H=K^Wfc-K=*-«r* 



I I I. 



■ I , I 1 



I I I I 



I 1 I I I I I I I I 1 I I ■ I 



15 



20 



25 



30 



I I I I ll I 1 1 

35 



-LI I 



! I 



JL-L 



H — M M- 



I 1 ' I 



40 

ALPHA CDEG3 



45 



50 



55 



60 



CONF IGURATICN 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076. 7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - W- 375.0 IN. 



REFERENCE Oir-ENSICNS 
WINS AREA SW • 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
H.A.C. CW - 39.560 FT. 

8COY LEN3TH L9 - 1290.3 IN. 





ALPHA (OEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


neL?a (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEE 


D6RAKE AXIAL FCRCE INC! 


3. 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00031 


0.00024 


0.00018 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


0.00069 


0.00052 


0.00035 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


0.00155 


0.00079 


0.00053 


0.00010 


0.00003 


0.0 


0.0 


0.0 


70.000 


0.00278 


0.00127 


0.00092 


0.00020 


0.00007 


0.0 


0.0 


0.0 


87.200 


0.00543 


0.00268 


0.00219 


0.00138 


0.00068 


0.0 


0.0 


0.0 



ENGINEER ^sb 
OATE__]£L-f£r!g> 



FIGURE 4.1.1.2- 90 

FFFFPT flF SPEEDERAKE 



4.1.1.2-94 



SD72-SH-006C I M 



€> 



Rockwell International 

Space Division 



ir 



MACH NUMBER = 20. 000 

• 08 ' i I ! I I I I I i I I i I I | i I 



DELSB CDEGD 

50 100 

| I I I I | I I I l | 



ca 
en 

< 

a 



.06 



.04 



.02 



■ F=3= 




I I I I i i I I i I I M i I i I i i 



-.02 



I 1 I 



I I I I 



A -LA . -JL- 



J__L 



1...1 1 .1. 



M IL. 



JL_J_ 



■10 



10 15 

ALPHA CDEG3 



20 



2S 



30 



35 



CONFIGURATION 




BASEL IfC CRB1TER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » F5 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO '- BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZP - W. 375.0 IN. 


M.A.C. CW " 39.560 


FT. 




BODY LENGTH L8 = 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


0ELS3 (OEG) 


A 


B 


C 





E 


F 


G 


H 






SPEE 


DERATE AXIA 


L FORCE I NCR. 






0.0 


-0.00207 


-0.00221 


-0.00210 


-0.00114 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00079 


-0 . 00084 


-0 . 00080 


-0.00043 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00055 


. 00063 


. 00068 


0.00C54 


0.00041 


0.00031 


. 00024 


0.00018 


45.000 


0.00102 


0.00123 


0.00130 


0.0011! 


0.00088 


0.00069 


0.00052 


0.00035 


55.000 


0.00254 


0.00289 


0.00300 


0.00276 


0.00228 


0.00155 


0.00079 


0.00053 


70.000 


0.00557 


0.00631 


0.00640 


0.00549 


0.00425 


0.00278 


0.00127 


0.00092 


87.200 


0.01008 


0.01150 


0.01170 


0.01007 


0.00797 


0.00543 


0.00268 


0.00219 



ENGINEER t^l? 

OATE_Jo=-3r^SL 



FIGURE 4.1.1.2-91 

EFFECT OF SPEEOBRAKE 



4.1.1.2-95 



SD72-3H-CCeC JM 



0& 



Rockwell International 
Space Division 



J_~ 



MACH NUMBER 

■08i i i i | | | N | I | 



20.000 



DELSB CDEGD 

50 100 

1 I I I I I I I I I I 



°9 
en 

< 

u 

a 



.06 



.04 



.02 




.02 



J_L.L 



aSBig^S ^ir^ 7 ?^ »=*&&■ 



I I I I I 



l I I I 



TT 



i i i m 



i i i i I i i i i 



i 



y^jtifr^L i ^K -i j a . . I K LftL MLM O r H 



I I I I 



_L_L 



44— H M- 



I I I 



15 



20 



25 30 35 M) 

ALPHA CDEGD 



45 



50 



50 









CONrI 


GLRATI 


BASELINE 0R8ITER VEHICLE 




CENTER OF GRAVITY 


XO 


- FS 


1076.7 


IN. 


OR 


YO 


- a. 


0.0 


IN. 


MCt€NT REFERENCE 


ZP 


- u. 


375.0 


IN. 



REFERENCE Dlf^NSIONS 
WING AREA SW - 2690.00 SQ.FT. 
MING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



DELSB (PEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



ALPHA (PEG) 



15.000 

F 




40.000 
K 



45.000 

L 



50.000 
M 



0.0 

0.0 

0.0 

0.00031 

0.00069 

0.00155 

0.00278 

. 00543 



0.0 

0.0 

0.0 

0.00024 

0.00052 

0.00079 

0.00127 

0.00268 



SPEEOeRAKE AXIAL FORCE INCR 



0.0 

0.0 

0.0 

0.00018 

0.00035 

0.00053 

0.00092 

0.00219 



0.0 

0.0 

0.0 

0.0 

0.0 

0.00010 

0.00020 

0.00138 



0.0 

0.0 

0.0 

0.0 

0.0 

0.00003 

0.00007 

0.00068 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.0 
0.0 



0.0 



ENGINEER^^ 
DATE jgjIJEjg 



FIGURE 4.1.1.2-92 

FFFFCT OF SPEEOBRAKE 



4.1.1.2-96 



SD72-SH-CC6C 1 M 



Space Systems Group 



* 



Rockwell 
International 



ALPHA CDE6) 
20 



HO 



•030 , | | | 



.025 



< 
a 




HO 60 80 

THETA (DEG) 



100 



CONF 1GURATI0N 



BASELINE ORB ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO = BL 0.0 IN. 

MOMENT REFERENCE ZO = 14. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW * 2690.00 SQ.FT 
WING SPAN BW - 7B.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 



ENGINEER i>£\£>_ 

DATE_\_q-_i?_;.; i _'L 



FIGURE 4. 1.1.2- V3 
LANDING GEAR AXiAL FORCE COEFFICIENT INCREMENT 



J HO 















THETA 


(OEG) 








0.0 


1 .000 


H.000 


10.000 


23.000 


53.000 


83.000 


99 . 000 


ALPHA ( DEG ) 


A 


B 


c 


D 


E 


F 


G 


H 






LANDIN 


JG GEAR AXI^ 


*L FORCE CC€ 


FFIC 






-10.000 


0.0 


0.00155 


0.00520 


. 00844 


. 1 364 


. 02078 


. 02663 


. 029S8 


-5.000 


0.0 


0.0014 1 


0.0OH67 


. 00760 


0.01227 


0.01870 


. 02395 


. 02687 


0.0 


0.0 


0.00120 


0.00400 


. 00650 


0.01050 


0.C1600 


. 02050 


0.02300 


5.000 


0.0 


0.00109 


0.00361 


. 00586 


0.00948 


0.01444 


0.01850 


0.02075 


10.000 


0.0 


0.001 OH 


0.00347 


0.00563 


. 00909 


. 1 385 


0.01776 


- 0.01992 


15.000 


0.0 


0.00107 


0.00357 


. 00579 


. 00936 


0.01425 


0.0182S 


0.02050 


20.000 


0.0 


0.00106 


. 00354 


. 00576 


0.00930 


0.01416 


0.01617 


. C2039 


25.000 


0.0 


. 00 1 06 


0.00351 


. 00570 


0.00921 


0.01403 


. 1 79? 


0.02017 



,.1.1.2-9' 



bk-oCCC 1M 



/ 



4* 



Rockwell International 

Spaca OhrtMcxi 




1.1.2-93 



SD72-SH-0CCC IM 



^^m Rockwell International 

Soaca CivtMcwi 




Landing Gear Down 



^ A G*OUN(T A 

truer 



oaouNO A ntt 

SFMCT STUJaM 




/2 



=^ 



CONFIGURATION 

IISEU1C 3IIITCI YtHICU 

cintii o* <M*»irr [!,■'« 1971.79 

-OM4nr tiriiiNCl 't,"* 375.J9 

IEFEU«Ct 3IMIKI0U 

Aii« w*2IM.9Mi'' 

inn w "1.3H •< 

»*c ... 31514 * 

too* uxant l, ■ ISOJM >• 



5. = -30. 000 



S„ = -11.7' 



5 n =ALL 



AC^-j 




1.6 




i„ h/b 

X. 130S.44 
Z. 282.71 



HW %, 




Angi« of Attack, a ~ 0«gr««i 


A -H.ooa 


, 0.0 


c H.000 


3.000 


. 12.000 


, 16.000 | c 20.000 


H/b 




ln«r«m 


•ntal A* 


iol Fore* Ca«ffi«i«nt , ^Cao«mo «f»«<r 


9.029 


0.05229 


0.07200 


0.36613 


o.o7im 


0.05657 


0.02722 


0.01016 


0.030 ' 


0. OH 350 


0.06030 


0.05112 


0.05943 


. 04530 


. 03908 


0.02167 


0.10O 


0.02610 


0.03330 


0.03333 


0.03686 


0.03084 


. 04250 


. 02785 


0.2X30 


0.01269 


0.01990- 


0.01397 


0. 01096 


0.00220 


0.00619 


, 0.0038t 


0.300 


0.00663 


0.01 140 


0.00644 


0.00318 


-0.00150 


. 00399 


-0.00275 


0.300 


0.00198 


0.004HO 


0.00143 


-0.00008 


-0.00307 


-0.00123 


-0.C0549 


t.oao 


0.00091 


0.00100 


0.0 


-0.00026 


-0.00063 


0.00027 


-0.00086 


1.500 


0.0 


1 0.0 


0.0 


0.0 


0.0 


0.3 


0.0 



UVlSIO: 



Figur» 4.1.1.2-95 

GROUND EFFECT 



3 



4.1.1.2-99 



SD 



... - O i 



-1-CC6C 1M 



tfft 



Rockwell International 
Space Qvisicn 



Landing Gear Dawn 




A C As»auN<T A «aouNO C AMg 



k <3«OUN0 
WMCT 



trnct 



STMAM I 




CONFIGURATION 

HilVH 9IIITEI tfllCU 



S.s-20. 000 



8„s-ll.7' 



CINfH a* 9MMnrr if,"! UTIJfl 
OQMIHI IfMliNCI tt,»>l 1TWI 

UFUEXCt .31MCMIMS 

in* s,* 719H x 

*« ._■ 3liHN 

■ear lotam l, • I29UM ■• 



S,.= ALL 



'Si 



ACao 8 



.oa 




1.5 



\wtl6HTS 
•VAN 



♦ .000 



3Z 



Angle of Attack, « ~ Degree* 



0.0 



c H.OCO 



o a. ooo 



8 12.000 If tS.000 c 80-000 



Incremental Axial Farce Coefficient , A^Ao^no ;»«cr 



tNOIWfll' 

OAT* //3-/+-ZZ 
MVISED 

V 




Figure 4.1.1.2- 44 

GROUND EFFECT 



4.1".T72-1C0 



SD72-SH-0C60 1M 



jpl^Jf Rockwell International 
Spac» Division 




Landing Gear Down 



*<3*OUHO "G»CUNO « ;*" I 
ifftC T JfMCT 3T8IAM ] 



^ C A G » OU MO" A G»OUNo" C AM!! 




S, = -15.000 



s&<f 



S„ = -11.7« 



^ 



CONFIGURATION 



^ 



ItStUKC SMITH UHICU 

3.3J 

175-00 






cintii a» ai*»irr 
01 

MOMfNt tlflMNCI 

UFEKHCl .1WCMI0M 

ifu< v.* "1.35* it 



■OST lltMTM 



3J.SM I 



5,.= ALL 



. .OH 



^ C AC! 




!•'«'•"«• Painf 




HeiGHV" 
•VAN 

h/b 

0.025 
0.050 ' 

a. too 
a. aoo 

0.200 

o.sao 

1.000 
1.500 



{NGINIER^ 
0>TI: /S 
UVISED- 



**' 



•/^-7r 



Angle of Attack, a ~ Oegreei 



A-H.OOO 



0.0 



c ■♦.ooo lo'a.ooo j 8 la.ooo j> ia.sao | q w.ooo 



0.CW522 
0.0H7O7 
0.03975 
0.02193 
0.01178 
0.0 OH 33 
-0.0005S 
0.0 



Incremental Axial Pore* Coefficient , A^Aghno 'fie: 



0.09030 
0.0X510 
0.0353O 
. 02050 
0.01200 
0. CI 0530 
0.0 
0.0 



0. 0*398 
0.03781 
0.02712 
0.01671 
0.01003 
0.00353 
0.00007 
0.0 



0.02713 

0.02357 

0.01862 

0.01178 

. 007 1 3 

0.00317 

0.0 

0.0 



0.01019 
0.01071 
0.01005 

0. 0528 
. 00235 
0.30061 
-O.0OOH2 
0.0 



-0 . 00995 

-0.00175 

0. 00490 

0.00220 

-0.00253 

-0.00271 

-0.30110 

0.0 



0.00506 
0.01019 
0.00852 

0.0004 I 
-0.30429 

-0.30473 
-0.00205 
0.0 



figure 4.1.1.2-97 

GROUND EFFECT 



4.1.1.2-lCl 



SD 



■ CCcC 1M 



pFl^| Rockwell International 
Space dvisaon 



Landing Gear Oown 




AC A 



— C — C 

a*ouNo" a g»ouno A«« 

!M«CT «"«CT 5TWAM 




5.= -10. 000 



8„ = -U.7* 



^ 



CONFIGURATION 

I1ULIK OIIITH VEHICLE 

C4NTH of aimrr > i."t II7IJB 

o» < '• • •* S.M 

■OHM IWttfKI 1(,**a 373.SI 

UFCHKCt .3HKMIMS 

W< I, » iliJO H 

tout iinarn l, • I23UM « 



5 U = ALL 



S\ 



A<* 



at 



.06 



.OH 



.02 



-.02 



.OH 



~l 1 1"" 


i i i 


i i i 


I i I 


"II! 


■ i ■ I 1 


T i™r^ 


I 1 ! 


— 














- 


_ \A^ 














- 


- *0*il 














- 


- \xv 














• 


— ^^ 














- 




-J — 


u~" "j 






^-■nvrir* 




- 


Bri- _^— 




i p 








! - 


:A 














- 


y 














— 


y 














- 


_ 














- 


Iiii 


i i i 


1 1 .L..._ 


. L.__L J_. 


1 I 1 


i i i 


! 1 I 


1 1 ! 



0.2 



O.t 



0.6 



0.9 



1.0 



1.2 



I. 1 * 



l.S 




X. 130S.44 
Z. 282.71 



HCiOMT 

•si 

h/b 



•VAN 



0.029 
0.090 ' 
0.10O 
0.200 
0.300 
0.500 
1.000 
1.900 



£L 



SNGIN€I(l'^ 

OAlt- /*-/*- 77 
««m«in: 



.000 



A n gle of Attack, a ~ Degrees 



i o.a |c *-° ao 



.000 



0.0H082 
0.03658 
0.02733 
0.01H2S 
0.00818 
0.0OH6* 
0.00101 
0.0 



t 12.000 .16.000 | q 20.000 
Incremental Axiol Force Coefficient f &Caq« n q ■fftcr 



O.OH380 
0.0395O 
0.03050 
0.017SO 
0.01150 
0.00530 
0.00100 
0.0 



0.03730 
0.0318H 
0.02368 
0.01357 
0.00843 
0.00619 
0.00100 
0.0 



0.01234 
0.01203 
0.01127 
0.00831 
0.00571 
0.00523 
. 00099 
0.0 



-0.001H3 
0.00096 
0.00223 
0.00307 
0.002SS 
0.00389 
. 00077 
0.0 



Figure 4.1.1.2-96 

GROUND EFFECT 



3 



-0.02351 

-o.o ma 

-0.00369 
0.00073 
0.00052 

-0.000HO 
. 00089 
0.0 



-0.00270 

0.00071 
-0.00017 

0.00119 
-0.00379 
-0.00380 

0.0008S 

0.0 



J' 



4.lYl."2-Me 



»fo) 



Rockwell International 
Soaca Division 



Landing Gear Down 



fZ 




sC 

<3*CUN0 „.., T 



^ AfljauNO A 0»O 



UNO C A«(! I 
KT 5TSUAM I 




3- =-5. 000 



8„»-u.r 



CONFIGURATION 

liSUllC 900ITM umcit 

cinmi a* a**»irr j i."i 1(71.79 

si <".«•» o.dd 

M3M4NI iihmnci ':.•«* J7S.80 
ICFUtlCE JIMMSIMS 

um W « 2111.901 «• 

i>«m v»« "lOH » 

M .„• lliHi. 



S 5J = ALL 



A c Agj 



.02 




-.03 



1.6 




X. 1506. a* 
r. 282.71 



- 
HtlGHT^ 

h/b 


Angle o* Attack, a ~ Degree* 


A -*.000 


1 o-o 1 


c H.000 


O 8.000 


1 12.000 |f 16-000 | 


G 20.000 




Incremental Ax 


ial Fore* Coefficient , &Ca<3«no tmcr 


a. oss 


0.02953 


0.03610 


0.03032 


0.00817 


-0.01434 


-0.02599 


-0.03100 


3.030 


0.02969 


0.03240 


. 02698 


0.00989 


-0.010m 


-0.01922 


-0.00697 


0. 100 


0.02302 


0.02550 


0.02000 


0.00919 


-0.00197 


-0 . 00727 


0.00361 


0.200 


0.01546 


0.01440 


0.01092 


0.00670 


0.00110 


0.00043 


0.00214 


0.300 


. 0Q82S 


0.00920 


0. 00562 


. 00332 


0.00167 


-0.00133 


0.0O 178 


0.500 


0.00130 


0.00450 


. 00217 


0.00172 


0.00122 


-0.00430 


-0.00171 


1.0 00 


0.00033 


0.00100 


. 00030 


0.00008 


-0.00048 -0.00207 


-0.00393 


l.SOO 


0.0 


0.0 


0.0 


0.0 


0.0 j 0.0 


0.0 



ENGINOIX: 

sate /a 

JfVlSID- 



£L 



-/?-?/ 



Figure 4.I.I.2- V9 

GROUND EFFECT 



4.1.1.2-103 



SD72-SH-CCCC iM 



%t 



Rockwdl International 

SpacaOMvon 




landing Gear Down 



tntcr t««CT "" 



ST»eAM 




CONFIGURATION 

iahuu mint fcmeu 

UHTII 4* OlMiff ( !.•»» IS7IJ9 

a« 

*om4ht mmM 

UFMCiCt.OIIUMiaiS 

<*** s.'!SM.0lli> 

i>m k»" 7L9H *• 



I.M 

J7J.fi* 



■oar umotm 



... lliHh 



5. = 0.0 



5„ = -11.7 < ' 



S.,= ALL 



'5» 



.OH 



ACft^i .02 




-.02 




f., h/fa 

X. IS06.J4 
Z, 2*2.71 



xT>AN 




Angle of Alt 


ack, a — Degrees 


A -*.0OO 


, 0.0 jc '♦•ooo | 


8.000 || 12.000 


f 16.000 |(j 20.000 




Incremental Ax 


ial force Coefficient ,ACAc*no muct 


0.039 


0.03H13 


0.02720 


0.01778 


-0.0OIB7 


-0.02019 


-0.02232 


0.00020 


0.090 ' 


0.030H9 


0.02H6O 


0.01651 


0.0003H 


-0.01HS3 


-O.0I88H 


-0.00170 


a. loo 


0.02391 


0.0 1990 


0.01393 


0.00227 


-o.oc6sh 


-0.01039 


0.00173 


0.200 


o.omm 


0.01270 


0.00887 


0.00388 


-0.00088 


-0.002H8 


0.002m 


0.300 


0.00663 


0.00720 


0.0OS23 


0.002HH 


-0.00221 


-O.OOtll 


-0.00008 


0.300 


0.00133 


0.00190 


0.00006 


-0.00122 


-0.00351 


-0.00357 


-0.00««03 


1.000 
] 1.900 


-0.00083 


-o.ootso 


-0.00200 


-0.00198 


-0.00188 


-0.001S8 


-0 . 00205 


0.0 


0.0 


0.0 


1.0 


0.0 


0.0 


0.0 



tNOINflt'.. 

pATt- sa 

UvUlO' 



iL 



-M-77 



Figure 4.1.1.2-100 

GROUND EFFECT 



4 I! /l i 2-3233 



SD72-SH-0C6G I'M 






Rockwell International 

SoacaOivBioo 




Landing Gear Down 



tZ 



SfFlCT !FfKT 5T«AM 




CONFIGURATION 

ll»ll*C 9IIITEI iCHICU 

ciHut o» ojA.irr , i,«<« HJU8 

0» J T. a u 3.J0 

aOlUHT lUIIIHCI 'l»«w» 175.30 

uhusm amcxsuM 

IHN *»■ "1.351 '• 

•ii ,„» ILiHh 

mot iiKorw ;, ' 1 214.348 .. 



S, = 5.000 



S„ = -11.7- 



5..= ALL 



^C A , 



.OH 



.02 



d 



-.02 



.OH 



— [—1 1 


1 1' 1 


— i — |— r 


i I i 


— r i i 


"■■i 1 1 


1 II 


"■ 1 II 


N 


^ 


==-— 




jj— ■» • -— 


p^^ 


BUV T "^Z^^M"ff 


1 1 1 1 1 I.I 




==S=i 




1 ,1 . .1 


! 11. 


ill 


ill 


1 ! 1 . 


1 1 1 


1 L 1, .. 


1 1 1 



0.2 



0.H 



0.8 




0.9 

!•/**«*<• Pmint 

,., h/b 

X, 1504.44 
Z. 282.71 



1.0 



1.2 



1.4 



l.S 



h/b 


Angle of Attack, OS — Degrees 


A -*.000 


i o-o 1 


c h.ooo 


o s.ooo 


1 12.000 


t 16.000 


,- 20.000 




Incremental Axial Fore* Coefficient , ^Ca G jno «mi<;t 


0.029 


. 02735 


0.02430 


0.01293 


-0.00505 


-0.02026 


-0.02783 


-0.01988 


. 0.050 ' 


0.02565 


O.0219O 


0.0I1S8 


-0 . 00288 


-0.01699 


-0 . 02497 


-0. 01341 


a. too 


0.02096 


0.01T70 


. 00986 


-0.00029 


-0.01073 


-0.01687 


-0.00203 


0.290 


0.01317 


a. 01090 


0.00619 


0. 00 164 


-0.00366 


-0.00563 


O.0OIIS 


3.300 


0.00833 


0.00740 


0.00396 


0.00140 


-0 . 00050 


-a. 00343 


-0.00281 


0.500 


0.00332 


0.30230 


0.00013 


•0.00119 


-0.00186 


-0.00524 


-0.00693 


1.000 


-0 . 0002S 


0.0 


0.0 


-0.00028 


-0.00125 


-0.00276 


-0.00410 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



OATE /3 
X6V1SEO: 






Figgre k. 1.1. 2-101 

GROUND EFFECT 



"4.1.1.2-105 



SD72 -Si ;-ccec IM 



^1^8 



flockwdl International 
SpacvONirion 



Landing Gear Down 




(fc 



AC A 



GltOUNO 
(FMCT 



~ c — c 



IMICT 



STMAM 




CONFIGURATION 

llUlllf 3IIITEI limit 

cinrti o# «A»irr > t,«<> U7I.70 

31 )'."«. I.M 

•MMMNf IIMUNCI tt.»* 17S.M 

UfEUUtt 3UUHSIQM 

u»» W2SM.AMH' 



... 3L}M» 

wo* i0to» i« > 12MJJM .. 



5, = 10. 000 



5„ = -11.7' 



5„= ALL 



A<^o f - 02 




-.02 



-.OH 




u, h/b 

Z. 2S2.71 



•VAN 
*/b 



0.023 
8.030 ' 

a. too 

0.200 
0.300 
0.3CO 
1.000 
1. 300 



AngU of Attack, a ~ 0«gr««« 



.000 



0.0 



C H,000 



9.000 



5 12.000 



t i«.ooo c ao.ooo 



I ncr«m«ntol Axiol Fore* Co«ffici«<it f A^Aono »>wct 



0.03492 
0.03068 
0.02239 
0.01131 
0.00355 
-0.00109 
-0.00OS3 
0.0 



0.02620 
0.0246O 
0.01930 
0.01090 
. 00460 
0.001 10 
0.0 
0.0 



0.0CS25 

0.00653 

0.00742 

0.003«»1 

0.00278 

0.00083 

0.0 

0.0 



-0.01368 
-0.01013 
-0.00456 
-0.00087 
-0.00024 
-0.00O27 
0-0 

r.o 



-0.02S01 
-0.02168 
-0.01349 
-0.00612 
-0.00143 
-0 . 00090 
-0.00021 
0.0 



-0.03411 
-0.03017 
-0.02048 
-0. 00844 
-0.00269 
-0.00223 
-0.00053 
0.0 



-0.02189 

-0.01704 

-0.00718 

0.00074 

0.00030 

-0.00413 

-0.00103 

0.0 



twain I in & 

OATl: W-/9-77 



Figure 4.1.1.2-ili 

GROUND EFFECT 



"4. 1.1 "."2-104 



SD72-SH-0060 1M 



&^ 



Rockwell International 
Spaca Division 




Landing Guar Down 



AC A 



G0.O 
EfMCT 



UIHlT A G»OUN0 Af«EE 

EFfECT ST8EAM 





5,= 15.000 



S„ = -U.7« 



CONFIGURATION 

MIEliM OMITM UHiCU 

cintii o# 3JA»rr ji,<n 1071.71 

gi <% *u 0.30 

MOMfNr iiMHMCt <(,•<•* 375.30 

ICFEUDCe 3IMCHS10flS 

U!A w« 2190.300'.' 

i»»k *_« 71.356 'f 

M .. « ILiiOx 

tap* vtMorw i 9 « !Z9fl.j00 <• 



^ 



5«= ALL 



^ C Age .02 




-.02 



-.04 



1.6 




tt«f«r«nc« '•i*t 

f.r h/b 

X, 1506.34 
Z. 282.71 



•Van 

h/b 


Angl* of Attack, a — D«gr««» 


a -h.0OO 


» a." 1 


c H.000 | 


O 8.000 


( 12.000 


, 18.000 


G 20.000 




lner»m«ntal Axial Forct Co«f fiei«nt , AQAg»no fffECT 


0.025 


0.04254 


. 02990 


0.00769 


-0.01052 


-0.027H3 


-0.04!?3 


-0.03412 


0.050 ' 


0.03647 


. 02670 


0.00834 


-0.00731 


-0.02176 


-0.03375 


-0.02592 


o. too 


. 02632 


0.01990 


0.00755 


-0.00487 


-0.01 666 


-0.02506 


-0.01696 


0.300 


0.01042 


0.01100 


0.00739 


0.00142 


-0.00497 


-0.01 1*3 


-0.004£4 


0.300 


0.00306 


0.00630 


. 00655 


0.00466 


0.00036 


-0.00018 


0.00407 


0.500 


-0.00069 


0.00190 


0.00263 


0.00155 


-O. 00151 


-0.00275 


-0.00232 


1.000 


-0.00070 


0.0 


0.0001H 


0.0 


-0.00062 


-0.00165 


-0.00342 


] 1 . 500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



ENOINEEH-_ 
OATE /0 






HtVlSEO: 



Figur* 4.1.1.2-103 

GROUND EFFECT 



4.1.1.2-107 



Rockwell International 

Spac« Division 



CO 

< 



-10 



-20 



-30 



-40, r 



-50 
1X10 



-■ 1 ■ 1 


i Mill 


- '■ f ,,- l — T FT ITT 


,,.., r 1 ,111,1 


i i r\ k \ i i i i u 


_ 








/ - 


- 








/ - 


- 








/ — 


_ 








/ 


— 








/ - 


— 








/ - 


- 








/ — 


_ 








/ 


- 








/ — 


- 








( 


_ 






/ 


- 


_ 






/ 


— 


_ 






/ 


- 


^ 






// 


— 


1 








- 


_ 








- 


_ 








— 


1 


1 I ! 1 1 1 


1 1 1 1 1 II I 


1 1 1 1 1 1 1 1 


i i i i M i r 



-07 



1X10 



•06 



IX10 -05 

PINF ' CPSID 



1X10 



-04 



COWIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO » FS 107S.7 IN. 

OR YO - a. 0.0 IN. 

MOCNT REFERENCE ZO - UL 375.0 IN. 



REFERENCE DIfCNSICNS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW » 39.550 FT. 

BODY LENGTH LB - 1290.3 IN. 



PINF (PSD 


•»» IMP 

Ib/n . 


AXIAL FORC 


I.000E-07 


-40.185 


3.000E-05 


■ -40.188 


1.000E-04 


-27.818 


3.60CE-04 


0.0 


4.500E-04 


0.0 


1.000E-03 


0.0 



1X10 



-03 






ENGINEER 



FIGURE 4.1.1.2-104 
AXIAL FORCE SURFACE IHP1NGEMENT.QQWN-FIRING 



4.1.1.2- 108 



SD72-SH-OG6C IM 



'1* 



Rockwell International 

Space Division 

L 



-.e; 



en 

u 

< 
a 




1X10 



1X10 



1X10 

PINF CPSI) 



1X10 



CONFIGURATION 



BASELINE 0RS1TER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - 8L 0.0 IN. 

MOMENT REFERENCE ZO « U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SU = 2630.00 SO. FT. 
WING SPAN BW =73.056 FT. 
11. A. C. CW * 39.560 FT. 

8COY LENGTH LB ■ 1 290. 3 IN. 



PINF (PSl ) 


<JA lb 


DE AXIAL F 


1.000E-07 


-0.580 


1.000E-05 


-0.560 


l .H00E-05 


-0.530 


3.000E-05 


-0.290 


4.500E-05 


0.0 


l.OOOE-04 


0.0 


i.OOOE-03 


0.0 



engineer"^ FIGURE 4.1.1.2-105 T „ 

dTiz jC L "jrr FLFVON AXIAL FORCE SURFACE TMPTNGFMFNT, DOWN-FIRING 



4.1.1.2- 109 



4* 



Rockwell International 

SpacaDMrion 

I 



CD 

< 

a 



-0.5 



-1.0 



■1.5 



-2.0 
1X10' 



•07 



1 1 1 1 


1 1 1 1 1 1 II 


1 1 1 1 1 1 1 1 


t mmm T 1 A l Illi" 


- 






/ 


1 1 1 1 ' 






- 






y 


I i i i i i l I 


1 1 1 1 1 ! 1 ! 


1 1 1 1 1 1 11 


1 1 1 ! ! 1 1 ! 



1X10 



-06 



1X1 0" 05 

PINF CPSID 



1X10 



-OH 



Cttf IGURATION 


BASEL INE 0R8ITER VEHICLE 


REFERENCE DIl-eNSIONS 


CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


UING SPAN SW - 78.056 FT. 


MC*£NT REFERENCE ZO - 14. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BOOY LENGTH LB - 1290.3 IN. 



PINF (PSI. 


3A lb 


3 $ tf n-d^ 


DBF AXIAL 


1.000E-07 


-1.730 


3.000E-05 


-1.730 


6.500E-05 


-I .4H0 


1.000E-04 


-0.980 


2.000E-OH 


0.0 


H.500E-0* 


0.0 


1.000E-03 


0.0 



1X10 



-03 



ENGINEER "j^2_ 



FIGURE 4.1.1.2-106 
RODYFLAP AXIAL FORCE SURFACE IMPINGEMENT. D0WN-FIRIN6 



4.1.1.2-110 



V_^ 



SD72-GK-CCCC I M 



* 



Rockwell International 
Spaca Division 

I 



OJ/OINF 
.1 



"3 

< 




30 35 

ALPHA CDEG) 





ALPHA (DEO) 


l/.buO 


2^.500 


27.500 


32.500 


38. oO 


OJ/QIU 7 


A 


B 


C , 


D 


E 




AXIA 


_ t-liHtc Jl. 


X 




0.0 


0.0 


0.0 


0.0 


0.0 • 


0.0 


. 0050 


-0 . 00246 


-0 . 00353 


-0.00380 


-0.00368 


-0.00390 


0.0100 


-0.00451 


-0.00550 


-0.005S! 


-0.00598 


-0.00530 


. 0200 


-0.00830 


-0 . 0092 1 


-0 . 00S65 


-0.01011 


-0.00932 


. 0300 


-0.01168 


-0.01250 


-0.01340 


-0.01361 


-0.01245 


0.0400 


-0.01464 


-0.01564 


-0.01654 


-0.01655 


-0»015I6 


0.0500 


-0.01717 


-0.01828 


-0.01925 


-0.01697 


-0.01746 


0.0600 


-0.01930 


-0.02051 


-0.02150 


-0 . 02092 


-0.01932 


0.0700 


-0.02100 


-0 . 02227 


-0.02327 


-0 . 02244 


-0.02073 


0.0800 


-0 . 02228 


-0 . 02354 


-0 . 02454 


-0 . 02357 


-0.02169 


. 0900 


-0.02315 


-0 . 02429 


-0 . 02528 


-0.02437 


-0.02217 


0.1000 


-0.02360 


-0.02447 


-0.02547 


-0.02489 


-0.02217 


0.1100 


-0.02360 


-0.02447 


-0.02547 


-0.02516 


-0.02217 


0.1200 


-0 . 02360 


-0.02447 


-0.02547 


-0.02525 


-0.02217 


0.1300 


-0 . 02360 


-0.024H7 


-0 . 02547 


-0 . 02525 


-0.02217 


0.1400 


-0 . 02360 


-0.02447 


-0.C2547 


-0 . 02525 


-0.02217 



j£_ = /jM \(±2!-) n = 0.1543(|-) 



irij= moss flow rote 

Vj= exit velocity 

n r number of thruslers 



A,.,= lft r 
S r .,= 2690 ft 2 



A C A„ 



' A +A 



i Ul) 



*i 



*.&/♦*•&) 



Interpolate for (X '% not 
shown af(«\ calculation 
of given a's only. 



22.500 
27.500 
32.500 
33.750 



Ao 



k 1 



-O.OOOi 
-0.0015 
-0.0016 
-0.0012 
-0-0019 



-0.44SO 
-0.4130 
-0.4460 
-0.5130 
-0.4090 



axi ai refe J J^T 



<V*j MIN iH-u 



J. 0900 
1.2600 
1.7100 
3.5400 
1,550a 



TOT 

5.7300 

3.8300 

-7.7900 

■J.13PQ 



0.0050 
0.0050 
. 0050 
. 0050 
. 0050 



0.1000 
0.1000 
0.1000 
0.1200 
Q 1000 



ENGINEER 
CATE.„i,CZfcttS._ 



FIGURE 4.1.1.2-107 
AXIAL FORCE JET INTERACTION. DOWN-FIRING 



4.1.1.2-111 



#J* 



Rockwell International 

Space Division 



MJ/MINF 
.05 



.10 




to 



J5 



20 



25 30 



35 



40 



45 



MJ/H1^ 



0.0 

O.OOt 

0.005 

0.010 

0.015 

0.020 

0.025 

0.030 

0.035 

0.040 

0.045 

0.050 

l>. 055 

0.060 

0.065 

0.070 



06 <c;G> 



7.500 
A 



12.500 
3 



17.500 
C 



22.500 
D 



27.500 

E 



0.0 

0.00042 

0.00211 

0.00214 

0.00208 

0. 00193 

0.00170 

0.00138 

0.00098 

0.00048 

-0.00010 

-0.00010 

-0.00010 

-0.00010 

-0.00010 

-0.00010 



0.0 

0.0C023 

0.00117 

0.00137 

ff. 00 100 

0.00023 

-0.00075 

-0.00175 

-0.00259 

-0.00303 

-0. 00304 

-0.00304 

-0.00304 

-0.00304 

-0.00304 

-0.0030'* 



0.0 
-0.00007 
-0.00025 
-0.00072 
-O.00C83 
-0.00133 
-0.00208 
-0.00293 
-0.00376 
-0.004H2 
-0.00478 
-0.00478 
-0.00478 
-0.00478 
-0.00478 
-0.00478 



axial fcsce vii ,;r 



32.500 

F 



38.750 
G 



0.0 
-0. 00019 
-O.000S6 
-0.00193 
-0.00227 
-0.00277 
-0.00337 
-0.00398 
-0.00455 
-0.00500 
-0.00526 
-0.00525 
-0.00525 
-0. 00525 
-0.0052S 
-0.0C52S 



0.0 
-0.00027 
-0.00133 
-0.00266 
-0.00329 
-0.00397 
-0.00464 
-0.00529 
-0.00593 
-0.0C626 
-0.00653 
-0.00658 
-0.00658 
-0.00658 
-0.00653 
-0.00658 



0.0 
-0.00021 
-0.00104 
-0 . 00209 
-0. 00274 
-0.00349 
-0.00427 
-O.0C497-, 
-0.00550 
-0.00578 
-0.00569 
-0.00559 
-0.00569 
-0 . 00569 
-0.00559 
-0.00569 



0.0 
-0.00009 
-0.00043 
-0.0O0S5 
-0.00129 
-0.00172 
-0.00191 
-0.00215 
-0.00246 
-0.00278 
-0.00309 
-0.00309 
-0.00309 
-0.00309 
-0.00309 
-0 ■ 00309 



x --W&(f)(^?--*-™-^ 



AC* _ 



s exit velocity — fp» 
v^ s fr»e»trtom velocity ~fp» 
$, ~ nozzle hoJf angle of exit 



*m+»(hr+»(y 



ACQ3.M 



Ao 



ALPHA 



(DEO) 

7.500 
12.500 
17.500 
22.500 
27.500 
32.500 
38-^0 



M 



A 2 



a 3 \^AJ U J^'AX 



0.00200 
0.00020 
-0.00220 
-0.00200 
-0.00t70 
-0.00150 
-0 .00210 



0.03140 
0.29190 
0.29000 
0.07150 
-0.06740 
0.00670 
. 08000 



-18. 95053 

-i6.oo:;o 

-7.36CC0 

-3.42CC0 
-7.80CC0 
-3.67C.0 



245.34760 

184.00000 

92.50000 

56.30000 

124.00000 

31 .20000 



0.00500 
0.00500 
0.01000 
0.01000 
0.01000 
0.01000 
0.02000 



0.045C0 
. 04500 
. 04500 
. 05000 
. 05000 
. C u 500 
0.04500 



«,, -1.0 

Interpolate for a's not 
shown af{<>\ calculation. 
of given a's only 



CAUTION: Polynomial curve-fit is valid 0KLY for the trass flow ratio range 
given in the above table. 

^' ^rfev- AXIAL^rE JFT'lNTER ArTTriN.STDE-riRlNG 

4.1.1.2-112 



DATE. 



SD72-SH~CCeC 1M 



* 



Rockwell International 

Space Division 

L 



< 

u 

Q 



.005 



-.010 



.015 



15 



OJ/GINF 
.1 




20 



30 35 

ALPHA CDEGD 



HO 



50 





AlFHA (Uttil 




17.&0D" 


az.bou 


27. SOU 


3<f.bOU 


38.750 


cu/oif^" 


A 


B 


C 


D 


E 




AXiAL t-OkO. Jl , 


^ „ „ 




— oo — 


0.0 


0.0 


0.0 


0.0 


0.0 


. 0050 


-0.00019 


-0. 00073 


-0.00131 


-0.00129 


-0.00123 


0.0 1 00 


-0.00036 


-0.00116 


-0.00191 


-0.00185 


-0.00166 


. 0200 


-0.00092 


-0 . 00206 


-0.00312 


-0.00300 


-0 . 00253 


0.0300 


-0.00173 


-0.00300 


-0.00431 


-0.00416 


-0 . 00342 


0.0400 


-0.00272 


-0.00298 


-0 . 00549 


-0 . 00532 


-0.00431 


. 0500 


-0.003S2 


-0.00500 


-0.00655 


-0 . 00648 


-0.00521 


. 0600 


-0.00497 


-0 . 00606 


-0.007d 1 


-0 . 00764 


-0.00613 


0700 


-0.00610 


-0.30715 


-0.00995 


-0.00881 


-0.00705 


. 0800 


-0.00714 


-0 . 00830 


-0.01 OOE 


-0.00997 


-0.00798 


0.0900 


-0 . 008C4 


-0.00947 


-0.01121 


-0.01 114 


-0 . 00893 


0. 1000 


-0.00872 


-0.01 069 


-0.01231 


-0.01231 


-0.00988 


0. ! 100 


-0.00912 


-0.01 059 


-0.01231 


-0.01231 


-0 . 00963 


0. 1200 


-0.00918 


-0.01 069 


-0.01231 


-0.01231 


-0.00S83 


0. 1300 


-0.00918 


-0.01069 


-0.01231 


-0.01231 


-0 . 00988 


0.1400 


-0.009'S 


-0.01 069 


-0.01231 


-0.01231 


-0 . 00996 



A = fe V— )" = 0.1543(f) 



irijS mo»* flow rate 

Vj= exit velocity 

n- number of thrusten 



A„,= lf|2 
S f .,= 2690 ft 2 



A c a„ 



= A + 



*.&)".&) , **.&)' 



ir^ . jesg' 



TTTsiS 
22.500 
27.500 
32.500 
3B.750 



Ao 



A 2 



-O.OUUl 
-0.0003 
-0 . 0007 
-0.0007 

-0-0009 



-0.0032 
-0.06V 1 
-0.1220 
-0.1150 
-0.0657 



AX 



A 3 (V*.U &/+-U 



W=i 



3701 

-0.1980 

0.0586 

-0.0115 

-0 . 0509 



3Z 



JTSCOT 
0.0 
0.0 
0.0 
JLfl 



070050 
0.0050 
0.0050 
0.0050 
0-0050 



0.1200 
0.1000 
0.1000 
0.1000 
Q-1QQQ , 



Interpolate for CC 's not 
shown a/'/et calculation 
of given a'% only. 



ENGll^ER H^Z_ 



DATE 



~ffif 



1±- 



FIGURE 4.1.1 
AXIAL FORCE JET 



. 2- 109 

INTERACTION. UP-FIRING 



4.1.1.2-113 



ED 72- -iH-CCe-C 1M 



<L* 



Rockwell International 

SpacaDlvMon 



OJ/OINF 



DE REF CDEGD 



UJ 

< 




30 35 

ALPHA CDEG: 



50 



oj/oiy 



TO" 
. 0050 
0.0100 
0.0200 
0.0300 
0.0400 
0.0500 
. 0600 
0.0700 
O.OSOO 
0.0900 
0.1000 
0.1100 
0.1200 
0.1300 
0-1^00 



17.500 
A 



"22-5W 



A LPHA i 



TTTJ 

-0 . 00089 

-0.00172 

-0 . 00320 

-0 . 00445 

-0.00548 

-0.00527 

-0.00584 

-0.00718 

-0 . 00728 

-0.00716 

-0.00530 

-0 . 00660 

-0.00680 

-0.00680 

-Q-QP69P 



i 



2T7 
C 



-0.00099 
-0.00187 
-0.00333 
-0.00456 
-0.00545 
-0 . 006C9 
-0.00651 
-0.00673 
-0.00681 
-0.00676 
-0 . 00653 
-0 . 00663 
-0 . 00663 
-0 . 00663 
-0-00663 



TCflAL FWCE 



W 



IT 

-0.00075 

-0.00144 

-0.00267 

-0 . 00372 

-0.00461 

-0.00535 

-0.00599 

-0 . 00653 

-0.00700 

-0.00743 

-0.00783 

-0.00783 

-0 . 00783 

-0.00783 

-0 . 00783 



E3£ 



32T5W 
J2 



35.750 
_E 



U70 
-0.00054 
-0.00112 
-0 . 00246 
-0.00406 
-0 . 00596 
-0.00822 
-0.01088 
-0.01399 
-0.01760 
-0.02174 
-0 . 02648 
-0.02648 
-0 . 02648 
-0.02648 
-0.02548 



TO 

-0.00134 

-0.00262 

-0 . 00499 

-0.00712 

-0.00902 

-0.01072 

-0.01221 

-0.01351 

-0.01464 

-0.01561 

-0.01643 

-0.01643 

-0.01643 

-0.01643 

-0.01S43 



-HfM(f£)"= - l543 <i) 



AC. 



(Tijr moii Flow rote 

VjS exit velocity 

n~ number of thrusters 



A r . t = 1ft 2 
S r .,= 2690 ft 2 



8. =-30 



= A +A 



<t>, 



i ('jz) 



+ A. 




Inrerpolote for a't not 
shown a^Set calculation 
of given a's only. 



ALPHA 




Ao 



M 



A 2 



&AAj*>/<i>-U 



0.0 

0.0 

0.0 

JUL 



-0.1330 
-0.2060 
-0.1550 
-0.1030 
-0-5750 



ry A^iAi^^ jnr 



.risen 

1.9700 

1 . 1500 

-0.9390 

1-3200 



"ffttf 
-5.7300 

-3.8300 

-7.7900 

_^-| 3QQ 



O.OT350T 
0.0050 
. 0050 
. 0050 
. 0050 



0.100U 
0.1000 
0.1000 
0.1000 

o.iooo 



O ATe__.i&<ifc '4Jj>- 



FIGURE 4.1.1.2-110 
ELEVON AXIAL FORCE JET INTERACTION. DOWN-FIRING 



4.1.1.2-114 



SD72-SH-OC6C 1 M 



#1* 



Rockwell International 

Spaca Otvwion 



AC 



A 5, 



.002 
.0 

-.002 

SSL. 



CDEG!) 



-30.000 



MJ/MINF 
.05 



-.004 



.008 



-.008 



I I I 



"I I 1 ' 



I I I I 



i i I 




I'll 



sOSfC^ 






/ /////// 



&£2 



/ // 



.1... I...1. 



i i ' I i i i 



3ftt$ -'-is ■a s -» ~ ' "*f!£fi, ', -V. 



I I ! I 






S?N WW 
V" \ t \ \ 



I ' I 



v \ \ \ N \ 

(.WW 
W\' 



T-T 



.U-V 



10 



15 



20 25 

U CDEGD 



30 



35 



40 



45 



.10 



i I i 



50 









ot ( OEG i 


" 






7.500 


12.500 


17.500 


22.500 


27 . 500 


32.500 


33.750 


MJ/MIt^ - A 


A 


8 


C 


D 


E 


r 


G 






0£ AXIAL FORCE Jl.Sf 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


-0.00027 


-0.00047 


-0.00050 


-0.00030 


0.0 


0.0 


-0.0002! 


0.005 


-0.00137 


-0.00235 


-0.00250 


-0.00151 


0.0 


0.0 


-0.00105 


0.010 


-0.00250 


-0.00375 


-0.00414 


-0.00257 


0.0 


0.0 


-0.00193 


0.015 


-0.00333 


-0.00439 


-0.00508 


-0.00324 


0.0 


0.0 


-0.00277 


0.020 


-0. 00402 


-0.00439 


-0.00545 


-0. 00360 


0.0 


0.Q 


-0.003-46 


0.025 


-0.00441 


-0.00439 


-0.00545 


-0.00350 


0.0 


0.0 


-0.00407 


0.030 


-0.00455 


-0.00439 


-0.00545 


-0.00350 


0.0 


0.0 


-0 . 00464 


0.035 


-0.00445 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0.00517 


0.040 


-0. 00442 


-0.00439 


-0.00545 


-0.00350 


0.0 


0.0 


-0.00569 


0.045 


-0.00442 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0 . 0C524 


0.050 


-0.00442 


-O.0C439 


-0.00545 


-0.00360 


0.0 


0.0 


-0.CCS32 


0.055 


-0.00442 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0.00622 


O.OSO 


-0.00442 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0 . 00=22 


0.065 


-0.00442 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0 . 00582 


1 0.070 


-0.00442 


-0.00439 


-0.00545 


-0.00360 


0.0 


0.0 


-0 . 0C622 



w. = >*.> »ml~rir^ _ :_. \ moo' \ ■*> i 



"58 - 

0, = 



ixif velocity — fpj 
freejtreom velocity — fpj 
nozzle half angle at exit 



ALPHA (C€G) 


ACa3,M!N,fiAX 


Ao 


A, 


A 2 


A 3 


<*AA, N r'A.W 


CE AXIAL FORCE Jl.ST 


7.500 


0.0 


-0.29910 


H.il3'0 


0.0 


. 00500 


. 03550 


12.500 


0.0 


-0.57E20 


22.58200 


-246.37460 


0.005GC 


0.01500 


17.500 


0.0 


-0.59300 


19.70000 


-184.00000 


0.00500 


. 02000 


22.500 


0.0 


-0.35300 


10.50000 


-92.50000 


. 00500 


0.02000 


27.500 


0.0 


0.0 


0.0 


0.0 


0.00500 


. 05000 


32.500 


0.0 


0.0 


0.0 


0.0 


. 00500 


. 05000 


38.750 


0.0 


-0.22900 


3. "3000 


-31.60001 


. 0C50C 


0.05000 



•Jl 



« I.O 



Interpolate for a's not 
shown a/Yet calculation. 
of given a'l only 



CAUTION: Polynomial curve-fit is valid ONLY for the mass flow ratio ranre 
given in the above table. 
rKjriK*TR n° FIGURE 4.1.1.2-111 

K^r^rfn-T_ FLEVQN AX I al force jet i nteractj GN . S I OE-F I RJ NG_ 

1. 1.1.2-115 



SD72-'*H-i'C6C 1M 



0^ 



Rockwell International 

Space Division 



^dos: 



-.002 



AC 



thsa. 



Kj, 



.004 



-.006 



.008 




MJ/MINF 

.05 



III) 



MM 



-' / •"»>■ ■■ i .-A-*-.- \ 









J I 



.'.'''*&?> 



V&&* 



*, * 




I ! 1..I. 



Mil 



I I M 



TT 



' I ' ' 



10 



IS 



20 



<* 



25 

CDEG) 



30 



40 



45 



.10 









at, (C 


EGi 








7.5C0 


12.500 


17.500 


22.500 


27.500 


32.500 


33.7=0 


KJ/MINT A 


A 


B 


C 





E 


F 


G 


C€ AXIAL FC.".E JI.SF 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


-0.00027 


-0.00046 


-0.00052 


-0.00031 


-0.00012 


-0.00027 


-0 . 0OC25 


0.005 


-0.00134 


-0.00228 


-0.00258 


-0.00154 


-0 . 00060 


-0 . 00 1 37 


-0.00127 


0.010 


-0.00251 


-0.00371 


-0.00437 


-0.00253 


-0.00103 


-0.00235 


-0.00232 


0.015 


-0.00352 


-0.00445 


-0.00553 


-0.00350 


-0.00134 


-0.00305 


-0.00317 


0.020 


-0.00437 


-0.00471 


-0.00517 


-0.00405 


-0.00156 


-0.00355 


-0 . 00355 


0.025 


-0.00505 


-0.00471 


-0.00645 


-0.00442 


-0.00174 


-0.00394 


-0.00439 


0.030 


-0.00557 


-0.00471 


-0.00545 


-0 . 00442 


-0.00132 


-0.00432 


-0 . 00480 


0.035 


-0.00593 


-0.00471 


-0.00645 


-0 . 00442 


-0.00192 


-0.00432 


-0.00511 


0.040 


-0.00612 


-0.00471 


-0.00S45 


-0.00442 


-0.00192 


-0. '00432 


-0.00534 


0.045 


-0.00616 


-0.00471 


-0 . 00645 


-0.00442 


-0.00192 


-0 . 00432 


-0 . 00552 


0.050 


-0.00616 


-0.00471 


-0 . 00645 


-0.00442 


-0.00192 


-0.00432 


-0.CC557 


0.055 


-0.00616 


-0.00471 


-0.00645 


-0.00442 


-0.00192 


-0.00432 


-0.00557 


0.060 


-0.00616 


-O.C0471 


-0.00645 


-0.00442 


-0.00192 


-0 . 00432 


-0 . 00557 


0.065 


-0.00616 


-0.00471 


-0 . 00645 


-0 . 0C442 


-0.00192 


-0.00432 


-0 . 00557 


0.070 


-0.00615 


-0. 00471 


-0.00545 


-0. 004*2 


-0.00192 


-0 . 00432 


-0 . 00557 









Vj = axil velocity — fps 

¥„ s freestream velocity — fpi 

0, = nozzle half angle a» exit 



*.. 



ALPHA tDEG) 


A0a3.MIN.MAX 


A 


A, 


A 2. 


A 3 


*VLU 


(*'A.U 


C£ AXIAL FORCE JI.SF 


7.500 


0.0 


-0.28410 


3.27690 


0.0 


0.00500 


. 04330 


12.500 


0.0 


-0.55530 


20.92740 


-246.34760 


0.00500 


0.02000 


17.500 


0.0 


-0.50300 


18.39999 


-184.00000 


0.00500 


0.02500 


22.500 


0.0 


-0.35200 


9.32000 


-92.50000 


0.00500 


0.02500 


27.500 


0.0 


-0.14000 


4.22000 


-56.30000 


0.00500 


. 03000 


32.500 


0.0 


-0.31900 


9.55000 


-124.00000 


0. 00500- 


. 03000 


38.750 


0.0 


-0.27700 


4.85000 


-31 .60001 


0.00500 


0.05000 



Interpolate for a's not 
shown a/Set calculation, 
of given a's only 



CAUTION: Polynomial curve-fit is valid CNLY for the niass flow ratio range 
given in the above table. 



ENG 
DATE 



mtr \P FIGURE 4.1.1.2-112 ^,„ Tl ^ 

: ^zfaff:: ELEVON AXIAL FORCE JET INT£RACTI0N.St0E-F_lR_[NG 



4.1.1.2-116 



■ 0>2 



-M 



«L* 



Rockwell International 

SpacaDivMon 



•°| I I I I I I I I I I I I I I I I I I I 



a^A, 



*(*&.) 



o 
u 

-3 
< 



8 




26 28 30 

ALPHA CDEG) 



CONFIGURATION 



BASELlrC CRBITER VEHICLE 

CENTER OP GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOttNT REFERENCE ZO * U. 375.0 IN. 



REFERENCE DirENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 



a/6 /<* ) ~ if ° own fir,n 9 i« f group u 
\ ' m > inoperative on on« side. 



ALPHA (DEG) 


(JCaji 


<W<*J 


AXIAL FORC 


17.500 
22.500 
27.500 
32.500 

38.750 


-0.H0000 
-0.3H000 
-0.39000 
-0.58000 
-O.H9000 



' »'rm, 



„<£><„. 



03 





ENGirCER 

DATE f /~C/jJ?. 



FIGURE 4.1.1.2-113 
AXIAL FORCE JET INTERACTION CARRYOVER. DOWN-F I RING 



4.1.1.2-117 



~o< :c iiv 



4* 



Rockwell International 
Space Division 




RJLATIVE WIND 



4.1.1.3 PITCHING MOMENT COEFFICIENT. The Orbiter Vehicle aerodynamic pitch- 
ing moment coefficient is defined in this section. The basic aero- 
dynamic pitching moment coefficient 
data are presented in three forms: 
1) as function of angle of attack 
and Mach number from M = 0.25 
through M ■ 20; 2) as a function of 
angle of attack and the_viscous 
interaction parameter (V<i) from 
0.005 (equivalent to M = 13.6) 

through 0.8 (equivalent to 300,000 feet of altitude); and 3) as a 
function of angle of attack and altitude from 300,000 feet through 
600,000 feet. Orbital aerodynamic characteristics are included in 
Appendix C. RCS jet thrust, thrust impingement, and flow field 
changes due to jet plumes are also included in this sect ion [k. 1 . 1 . 3J . 
Uncertainties associated with the pitching moment characteristics 
are available in Section 6.0. 



The RCS flow field interact 
to the total pitching momen 
since the terms due to Jet 
dynamic pressure and cannot 
tional manner. CAUTION sho 
In the flight regime where 
dynamic pitching moment (cf 
pi tching moment coefficient 
before adding the RCS flow 
B). 



ion data are presented as a contribution 
t (M) rather than the coefficient (C m ) 
thrust and impingement are independent of 
, therefore, be normalized in the conven- 
uld be observed when applying t^hese terms 
RCS is used In conjunction with the aero- 
. Section 3.6); 1 .e. , the aerodynami c 
must be converted to a .dimensional moment 
field interaction effect . (see .also Appendix 



The total pitching moment is: 
M total - q Sc C 



m TOTAL 
AERO 



+ M 



RCS 



*The total aerodynamic pitching moment coefficient about .65 percent of 
the body length (FS 1076.7, WL 375.0, BL 0.0) is .obtained by the 
fol lowing equation: 



m 



TOTAL 



- C + [AC 



+ AC ] llivo ,t AC + AC ■ + AC 



■basic 



AERO 



ELEVATOR ^AILERON 



BODY 
FLAP 



"RUDDER 



'SPEED 
BRAKE 



0.6JL g 



* r ££ + fc + AC 1 3£ + AC + AC + AC + AC 

C m. 2V L nv rru J 2V m HEX m lAN0ING ^ground ^siits 

a q M$B GEAR EFFECT POD 

BF 



*Rpfer to Appendix D when using digitized data. 

NOTE- The increment presented in Appendix E should be added to the total from 
above emulations to account for OV102 manufactur ,ng m.sal .gnment . 



4.1.1. 3-1 



SD'f-L'-SH-CCC-C 1M 



%$ Rockwell International 
Space Division 



where, 

C - Basic, full-scale, freestream, rigid- (Figures 4.1.1.3-1 

m BASic body pitching moment coefficient through -6) 

about 0.651b 

NOTE: 1. All control surfaces neutral 
except 6 SB ■ 25°. 

2. For Moment Reference CenCer 
other than , 6 5 L B , 

Ax - Az r 

C - C + sr- c - =- c 

m M Rc m o.6iL B c N c * 

where Ax = x MR £ io76.7inches 

Az - W 375i " ch « 

3. Moment transfer of (2) .applies 
to all fol lowing increments 
and/or slopes except as noted. 

Change tn pitching moment coefficient (Figures 4.1.1.3-7 
due to elevon (elevator), deflection, through -37} 
6 e , when inboard and outboard angles * 

are equal . 
NOTE: 1. Partial span factor, K m , to be(Figure 4.1.1.3-38) 
used for elevon-body flap 
interconnect flight system 
where 6 e is limited to ±5° 
and inboard and outboard 
angles are not equal . 



m 5LEVATOR 



8*8, o °. d »i • *° 

AC _ Change in pitching moment coefficient 

m AiiERON due to aileron deflection, <5 a . 



EVATG« 



A C - Change in pitching .moment -coefficient (Figures 4 1 1 . 3"39 

"Uooy due to body flap deflection, 6 BF through -/£) 

FLAP 

AC - change in pitching moment .coefficient (Assume zero) 

m RUD0ER due to rudder deflection, 5 r . 



4 - u '- 3 - 2 S DV2.S:--,-.:c.C ir. 



#1% 



Rockwell International 

Space Division 



AC » Change in pitching moment coefficient (Figures A . 1 . 1 . 3"73 

m5 . p D E A° c due to speed brake deflection, 6. . through -95) 

C ■ Change in pitching moment coefficient (see NOTE 1, C ) 

a due to rate of change of angle o' q 

attack, a, (per radian).* 

C - Change in pitching moment coefficient (Figures *i. 1.1. 3-100 

m q due to pitch rate, q, (per radian).* through -101) 

NOTE: 1. As presented herein, C = C 

r mm 

q q 

+ C and should be treated 
c 

as C 

m 

q 

AC « Incremental effect of speed brake/body (Fi gure k. 1. 1.3-102) 
m q flap on pitch damping- 



BF 



^M^H-'-Xw) 



^ Cm q ss =100 



tf=U.75 

NCTS: 1. For noraal simulations, use K sa ■ 0.5 

"-4 

2. For sensitivity studies, assume K ss can 
be either or 1. 

AC ■ Change in pitching moment coefficient 
mfLE * due to aeroelastic deformation. 



- AC m " (1 " ^)(c m - c ffl ^-(-i 1 )' %(c N - c N >; aSic 

o o o 

- (1 - nj(AC R +AC m ) - (l - T\ ) AC" 

e 

- (1 - n ) AC" - (i - n ) C« ff 

where the flexible (F) to rigid (R) ratios are 

n N - basic normal force (Figure k. 1 . 1 . 3-103) 
n - elevon (Figure ^. 1 . I . 3-104) 

*For rotary derivative transfer equations see NASA SP -3070, "Summary of. Trans- 
formation Equations and Equations of Motion Used in Free Flight and Wind Tunne 
Data Reduction and Analysis," Gainer, T. G. , and S. Hoffman, Langley Research 
Center, Hampton, Virginia (1972). 



' 1J ' 3 " 3 SD72-SF-0CCC 1M 



* 



Rockwell International 

Space DMwon 






V. 



- body flap (Figure ^.1.1-3 -105} 

- speed brake (Assume 1.0) 

- pitch rate (Figure A.l .1.3-106) 



and, AC' - flexible intercept at (Figure *». 1 . 1 . 3-107) 
o a - 

/ Ax *c \' 

(— =-) - Shift in aerodynamic (Figure ^ . 1 . I - 3-108) 

c center due to aero- 

elasticity. 

NOTE: I. Detailed discussion of aero- 
elasticity may be obtained 
from Append i x A. 

AC - Change in pitching moment coefficient (Figure *♦. 1 . 1 . 3"109) 

Landing due to extension of landing gear. 

Gf A« 

AC - Change in pitching moment coefficient (Figures A. 1.1.3*110 

m o«cuND due to proximity of ground, f (h/b) . through -119) 

ffftCT 

AC • Change in pitching moment coefficient * 

m suTs au e to addition of SILTS pod. 

for 

- -0.000635152 + 0.000881151 M - O.OOC17311? M 2 
for M < b.O 



zero 



for M > 6.0 



RCS flow field interactions have been subdivided into three compon- 
ents: 

1. RCS JET THRUST (subscript JT) 

2. RCS JET PLUME IMPINGEMENT (subscript IMP) 

3. RCS JET PLUME EFFECT ON FLOW FIELD (subscript Jl) 

The effect of the RCS may be described as a dimensional pitching 
moment (foot-pounds) in terms of the significant contributing elements 
by: 

u _ v ilu +*m +^M 1 =+q" Sc"tiiC ■*• iC + LZ 

HAP HAP 

+ AC ]., 

"DOWN ' 

PIKING 

C A«»'Ovf « 



;. 1.1.3-'* 



c r 7:. -v\- oct c im 



9 



Rockwell International 

Space Division 



where, 

Mj - Pitching moment resulting from number (cf. Appendix B) 
(n) of jets being fired (Reference 
data only) . 

0,G 

NOTE: 1. OJG - operating jet group 
(cf . Figure B-l) 

M su », - Pitching moment resul ting from jet im-(Figure k. 1.1.3-120) 

imp pingement or. Orbi ter Vehicle surfaces (s) 

- L [M su „ ' n"]- ft-lb 

OjG IMP 

am ■ Change in pitching moment due to (Figure 4.1.1.3*121) 

imp effect of impingement .on .elevon 

effectiveness. 



L[lr -«-«.]" ft - ,b 

ojg L e J 



- Change in pitching moment due to (Figure 4.1.1. 3-122) 

fiap effect of impingement on body flap 

effectiveness . 



am iody 



- Z \'£-- • " ■ CI ~ ft " ,b 

AC - Change in pitching moment coefficient (Figures 4.1.1.3-123 

m j< due to jet interaction. through -125) 

■ £ [ "»J 

AC - Change, in pitching moment coefficient 

m £iivoN due to jet interaction .effect on 

Jl elevon effectiveness. 

T [(AC L • (6/6. )°'"1 
oTg L mfi «-f- e e "" ^ 



4.1.1.3- 



SD7? -SH-006C 1M 



* 



Rockwell International 

Space Division 



AC. 



'IOOY 



AC 



NOTE: 1. Down-firing jets 

6 < 0", 6 - -30° 



5 > 0°, <5 - +10" 



2. Si de-f i ri ng jets 

6 < 0°, £ 
e e, EF 



6 > 0°, 6 
e e JEF 



3. Up-f i ring jets 



-3C° 
+ 10' 



(Figure A. 1 . 1 . 3-126) 
(Figure A. I .1 .3-127) 

(Figure *i. 1 . 1 .3-128) 

(Figure «t. 1 . 1 . 3-129) 



(No effect) 



Change in pitching moment coefficient 
due to jet interaction effect on body 
flap effectiveness. 



CJG L "KEF 

NOTE: 1. Down-firing jets 

<5, f <0', 6,F REf - -1^.25' 

2. Side-f i ring jets 

3. Up-f i ring jets 

- Effect of carry-over between left- 
m oowN anc j r ight-down firing jet groups due 

ca*«vove» to jet interaction. 



(Figure A. 1.1.3-130) 

(No effect) 
(No effect) 
(No effect) 

(Figure 14.1.1.3-131) 



2 SIDES 



r 3C "I _ 



,/OD 



NOTE: 1. $./$„- (C15^3/qjn 

2. This tern is zero when down- 
firing jet group is inopera- 
tive on one s i de. 

3. u~~77j - h [<-yao + V-J,o] 

where: < (:"7cJ < 0-°3 



1.3-6 



SD72 -SH-CCtC 1M 



Space Systems Group 



4* 



RocKwell 
International 



UJ 

a 



< 
i 
a. 




0.2 



0.4 



0.6 0.9 

MACH NUMBER 



CONFIGURATION 




BASELINE ORBtTER VEHICLE REFERENCE OINENSICNS 




CENTER CF GRAVITY XO =» FS 1076.7 IN. WIND AREA SW » 2690.00 


SQ.FT. 


OR YO » 8L 0.0 IN. WING SPAN 8W » 78.056 


FT. 


MOr-ENT REFERENCE ZO - W. 375.0 IN. M.A.C. CU » 39.560 


FT. 


BCOY LENGTH LB » 1290.3 


IN. 



ALPHA (PEG) 



m 



-10.530 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

40.000 

45.000 
50.000 
55.000 
60.000 



-D-25TT 



UThUO" 
_S 



U7SW 
_C 



MACH" 
0.8fld| 



0.03200 
0.03000 
0.02900 
0.02800 
0.02700 
0.02600 
. 02400 
0.02300 
0.02300 
0.02400 
0.01900 
0.01400 
0.01050 
0.01000 



0.03400 
0.03200 
. 03050 
0.02900 
0.02750 
. 02600 
0.02400 
0.02200 
0.02250 
0.02200 
0.01600 
0.00800 
0.01000 
0.01200 



4 »**»»*»**»1 ****** 
< »*********1 ****** 



- **•*•**•»*' ****** 



■ ********** 



"0.04000 
0.03650 
0.03470 
. 03300 
. 03C50 
0.02900 
. 02400 
0.02050 
0.02100 
0.01600 
0.00900 

-0.00400 
0.00600 
0.03300 



»•♦! ft 





PITCHING 



Nyr; 



6.05900 
. 04900 
. 04450 
0.04000 
0.03600 
0.03150 
0.02250 
0.01800 
0.01700 
0.00600 
-0.00600 
-0 . 00500 
0.00260 
. 08000 



ore 

K3"ENT_CCgF" 



#»♦»»»»»•»»»••»»» 



IHHIIHtlUHItHHIl 



. 06800 
. 05400 
0.04700 
0.04000 
0.03800 
0.03200 
. 02200 
0.01700 
0.01200 
0.C0050 
-0.01100 
-0.01000 
0.02000 
0.09000 



FiClENf 



■ XllOtllltlKII 



TT9W 

F 



_S 



"05T 

H 



oTOSOOd 

0.06100 

0.04500 

0.03500 

0.02500 

0.02250 

0.02000 

0.01500 

0.00750 

-0.00250 

-0.01000 

-0.00300 

0.02000 

o.osoao 



O.iOioO 

. 06700 

0.05300 

0.03800 

0.02200 

0.01500 

0.01200 

0.00400 

-0.00600 

-0.01800 

-0.02800 

-0". 03000 

-0.01200 

. 08700 



Oft IKK 



ft ft* ftftftft* 



0.12600 
0.08200 
0.06200 
0.04200 
0.02000 
0.0 

-0.01500 
-0.02700 
-0.04000 
-0.05000 
-0.05650 
-0.06000 
-0.03500 
0.07000 



>* * 
► ** 



1.4 



o.seo 

_! 



0. 14000 
. 09800 
. 07800 
. 05500 
0.03100 
0.00500 

-a. 0150a 

-0.03000 
-0 . 04200 
-0 . C5200 
-0 . 06300 
-0 . 07200 
-0 . 04700 
0.02000 



ENGINEER 2X?£i 
'0ATE„i.5S:^: 



FIGURE 4. 1.1. 3-- 1 
BASIC PITCHING MOMENT COEFFICIENT 



,.1.1.3-" 



SD 



H-CCcC JM 



3* 



Rockwell International 

SpmDMtfon 



LU 

o 



< 
X 
0- 




0.2 



O.H 



0.6 



0.8 



1.0 J.Z I* 

MACH NUMBER 



1.5 



1.8 



2.0 



CONFIGURATION 



BASELINE CR9ITER VOHICU 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

rt>€NT REFERENCE ZO - W. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA S-l - 3690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 
BODY LENGTH LB » 12 9Q,3 1M 



ALPHA (C€G> 



■10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

J5.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

HO. 000 

45.000 

M.000 



0.900 

F 



0.920 
_£ 



0.950 
H 



0.980 



MACH N-TfgR 



. 09000 

0.06100 

0.04500 

0.03500 

0. 02500 

0.02250 

. 02000 

0.01500 

0.00750 

-0.00250 

-0.01000 

-0.00300 

0.02000 

0.09000 

••••••• 



0.10100 

0.06700 

. 05300 

0.03800 

0.02 2 00 

O.OlbuO 

0.01200 

0.00400 

-0.00600 

-0.01800 

-0.02800 

-0.03000 

-0.01200 

0.08700 



*««••• 

••«»»• 




0.12600 

0.08200 

0.06200 

0.04200 

0.02000 

0.0 

-0.01600 

-0.02700 

-0.04000 

-0.05000 

-0.05550 

-0.06000 

-0.03500 

0.07000 



PITCHING 



1.050 



1.100 

K 



1.200 
L 



"1.300 

_a 



1.500 
N 



0. 14000 
0.09800 
0.07800 
0.05500 
0.03100 
0.00500 
-0.01500 
-0.03000 
-0 . 04200 
-0.05200 
-0.06300 
-0 . 07200 
-0.04700 
0-02000 
#•♦»**• 
•»•**•* 
••«»•«■ 
•♦•••• t 
♦• t t • •• 



HQrf-NT COEFFICIENT 



0.15800 

0.1IHO0 

0.08400 

0.05500 

0.02HOO 

-0.00300 

-0.02200 

-0.03400 

-0 . 04500 

-0.05800 

-0.07000 

-0.07700 

-0.06100 

-0.02300 

••••#•♦ 

IIDDI 



0.16250 

0.1)800 

0.08200 

0.04700 

0.01500 

-0.01050 

-0 . 02900 

-0.04000 

-0.04900 

-0.06200 

-0.07400 

-0.08100 

-0.06800 

-0.04200 



0. 16200 

0.11200 

0.07200 

0.03400 

0.00600 

-0.02000 

-0.04000 

-0.05400 

-0.06100 

-0.07200 

-0.08200 

-0.08800 

-0.08000 

-0.06400 

► »•« * •• 



0.14800 

0.09200 

0.05800 

0.02500 

-0.00100 

-0 . 02350 

-0.04400 

-0.060C0 

-0.07200 

-0.08300 

-0.09000 

-0.09300 

-0.09100 

-0.07700 

• ■ •♦ t« 



0.10300 

0.05000 

.03700 

.01400 

.00700 

.02500 

. Oh i 00 

. 05500 

-0.07000 

-0 . 08200 

-0. OS 100 

-0.09700 

-0.09500 

-0 . 08200 

« • • • 

• • • • 
*♦•« 

• • •• 

• • • » 



FIGURE 4. 1.1. 3-- 2 
BASIC PITCHING MOMENT COEFFICIENT 



4.1.1.3-8 



€> 



Rockwell International 



CM 

2 .1 -. 1 

I I I I I I I I \ 1 I I I I I 






< 

_J 
< 




-10 



5.5 



CONFIGURATION 



BASELINE CRB1TER VEHICLE 

CENTER OF GRAVITY XO - FS 10TB. 7 IN. 

OR YO - BL 0.0 IN. 

MOENT REFERENCE ZO - W. 375.0 IN. 



REFERENCE DlrOSICNS 
WING AREA SW • 3690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
H.A.C. CW - 33.560 FT. 

pn flY LENGTH LB - 12903 _JNL 




-10.000 

-5.000 

-8.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 
17.500 
80.000 
22.500 
25.000 
30.000 
35.000 
HO. 000 
45.000 
50-000 



0.16250 

0.11800 

0.08200 

0.04700 

0.01500 

-0.01050 

-0.02900 

-0. 04 000 

-0.04900 

-0.06200 

-0.07400 

-0.08100 

-0.06800 

-0.04200 



0.16200 

0.11200 

0.07200 

0.03H00 

0.00600 

-0.02000 

-0.04000 

-0.05400 

-0.06100 

-0.07200 

-0.08200 

-0.08600 

-0.08000 

-0.06400 



ENGINEER 






14800 
.09200 
.05800 
.02500 
.00100 
-0 . 02350 
-O.04H0O 
-0.06000 
-0.07200 
-0.08300 
-0.09000 
-0.09300 
-0.09100 
-0.07700 



0.10300 

0.06000 

0.03700 

0.01400 

-0.00700 

-0.02500 

-0.04100 

-0.05500 

-0.07000 

-0.08200 

-0.09100 

-0.09700 

-0.09500 

-0.08200 



>*«»«.«.«»4 ••••••••• 



i »*• »•**•«• • 



• «»•»»»».-» 



ENT COEF 
0.04200 
0.01750 
0.00800 
-0.00130 
-0.01300 
-0.02380 
-0.03360 
-0.03850 
-0.04300 
-0.04720 
-0.05160 
-0.05810 
-0.06150 
-0.06490 
-0.05180 






"NT 
0.00450 
-0 . 00800 
-0.01144 
-0.014S0 
-0.01940 
-0.02300 
-0.02480 
-0.02740 
-0.03100 
-0.03510 
-0.03950 
-0.04440 
-0 . 05000 
-0 . 05530 
-0.06640 






-0.01800 
-0.01 BOO 
-0.01850 
-0.01SOO 
-0.01S70 
-0.02050 
-0.02150 
-0.02250 
-0.02400 
-0.02700 
-0.03000 
-0.03HOO 
-0.03700 
-0.0*200 
-0.05400 
-0.06600 
-0 . 08300 
-0.10000 



-0.02940 
■0.02700 
-0.02550 
-0.02310 
-0.02100 
-0.01B30 
-0.01820 
-0.01830 
-0.01910 
-0.02010 
-0.02150 
-0.02310 
-0.02500 
-0 . 02780 
-0.03720 
-0 . 04850 
-0.05140 
-0.07580 



>«*•»«*#»« 



-0.03370 
-0.03070 
-0.02800 
-0.02480 
-0 . 02200 
-0 . 02000 
.01810 
.01660 
.01560 
.01520 
.01510 
-0.01550 

-o.onoo 

-0.01940 
-0.02700 
-0.03940 
-0.05300 
-0 . 06750 
-0.08330 



-0. 
-0. 
-0. 
-0. 
-0. 




FIGURE 4.1.1.3— 3 
BASIC PITCHING MOMENT COEFFICIENT 



4.1.1-3-9 



SD7--SH- CC6C 1M 



#1% 



Rockwell International* 

Spac* Division 



-.16 



CD 
O 



< 
X 




CONFIGURATION 

BASELINE 0R81TER VEHICLE REFERENCE: DIMENSIONS 

CENTER Of GRAVITY XO » F5 1076.7 !N. WING AREA SW • 2690.00 50. FT. 

OR YO » BL 0.0 IN. WING SPAN BW = 78.055 FT. 
MOrENT REFERENCE ZO - WL 375.0 IN, M.A.C. CW » 39.560 FT. 
B30Y LEN3TH t R » 1250.3 IN. 



ALPHA IDEG) 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

1 . 000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30 . 000 

35.000 

40 . 000 

45.000 

50 ■ 000 



2.000 



2.500 
P 



3.000 
__Q 



4.000 
R 



_WVyH 



N.J"- r .H 
5.0001 



e . ouo 

T 



0.04200 
0.01750 
0.00800 
-0.00130 
-0.01300 
-0 . 02380 
-0 . 03350 
-0.03050 
-0.0M300 
-0 . 04720 
-0.05160 
-0.05B10 
-0.06150 
-0 . 06490 
-0.05180 



0.00450 
-0 . 00800 
-0.01144 
-0.01480 
-0.01940 
-0.02300 
-0.02460 
-0.02740 
-0.03100 
-0.03510 
-0.03950 
-0.044H0 
-0.05000 
-0.05530 
-0.06640 



-0.0 1 BOO 
-0.01800 
-0.01850 
-0.01900 
-0.0)970 
-0.02050 
-0.02150 
-0.02250 
-0.02400 
-0.02700 
-0.03000 
-0.03400 
-0 . 03700 
-0 . 04200 
-0.05400 
-0.06500 
-0.08300 
-0.10000 



PITCH;!.;. r£_ 

-0.029-IO "" 

-0.02700 

-0 . 02550 

-0.02310 

-0.02100 

-0.01880 

-0.01820 

-0.01830 

-0.01910 

-0.02010 

-0.02150 

-0.02310 

-0.02500 

-0 . 02780 

-0.03720 

-0.04850 

-0.06140 

-0.075R0 



cnt cor.F 



0.03i70 
0.03070 
. 02800 
. 02480 
0.02200 
. 02000 
0.01810 
0.01660 
0.01560 
0.015=0 
0.01510 
0.01550 
•0.01700 

o.oie40 

0.02700 
. 039*0 
■0.05300 
•0 . 06750 
. 08330 



IC1ENT 



10.000 
_JJ 



15.000 
V 



20 . OOC 
w 



-0.03500 
-0.03280 
-0.03000 
-0 . 02700 
-0.0c 350 
-0.01900 
-0.01560 
-0.01250 
-0.009D0 
-0.00725 
-0.00493 
-0.00330 
-0.00400 
-0 . 00590 
-0.01350 
-0.02570 
-0.04290 
-0.06150 
-0.09190 



-0.03500 
-0.03280 
-0.03000 
-0.02700 
-0 . 02300 
.01900 
.01550 
.01200 
. 00970 
. 00780 
. 00500 
-0.00500 
-0.00620 
-0.008C0 
-0.01500 
-0.02600 
-0.04 100 
-0.06100 
-00B200 



0. 07500 

0.03280 

0.03000 

. 02700 

. 02350 

0.01900 

0.01560 

01200 

00370 

00780 

00500 

00600 

00620 

00900 

01500 

02500 

04100 

06100 

8200 



03500 
03250 
03000 
02700 
02350 
01900 
01560 
01200 
00970 
C0730 
0060G 
00600 
00620 



-o.ooeoo 

-0.01500 
-O.OrvOO 
-0.0m ICO 
-0.06100 
-0 . 09200 



ENGINEER. '^^i 



FIGURE 4.1.1. 3-- 4 

BASIC PITCHING MOMENT COEFFICIENT 



4.1.1.3-10 



*i* 



Rockwell International 

Space Division 



L 



ALPHA CDEG) 

20 30 40 



50 







CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE ZO = H_ 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB » 1890.3 IN. 





VBAR 


0.005 


0.010 


0.020 


0.040 


0.C60 


0.080 


ALPHA (DEG) 


A 


B 


c 


D 


E 


F 




VIS. F 


ITCHING MOM 


ENT COEFFIC 


I ENT 




20.000 


-0.00600 


-0.00600 


-0.00600 


-0.00600 


-0 . 00600 


-0.00600 


25.000 


-0.00800 


-0.00800 


-0 . 00800 


-0.00800 


-0.00800 


-0 . 00800 


30 . 000 


-0.01500 


-0.01500 


-0.01500 


-0.01500 


-0.01500 


-0.01500 


35.000 


-0.02600 


-0.02600 


-0.02600 


-0.02600 


-0.02600 


-0.02600 


40.000 


-0.04100 


-0.04100 


-0.04100 


-0.04100 


-0.04100 


-0.C4100 


45.000 


-0.06100 


-0.06100 


-0.06100 


-0.06100 


-0.06100 


-0.06100 


50.000 


-0 . 08200 


-0 . 08200 


-0.08200 


-0.08200 


-0.08200 


-0.08200 



ENGINEER NASA 
DATE ZZZZZZI 



FIGURE 4.1.1.3-5 
BASIC PITCHING MOMENT 



COEFFICIENT 



4.1.1.3-11 



SC 72-5H-CCCC 1M 



# 



Rockwell International 

Space Division 



ALPHA CDEGD 

20 40 60 

| "i I I I | I I t I | 



U 



.-.3 




-.4 
350000 



400000 . 450000 500000 550000 600000 

ALTITUDE CFT.) 



650000 



700000 



CONFIGURATION 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR Y0 - BL 0.0 IN. 

K>ENT REFERENCE ZO - U- 375.0 IN. 



REFERENCE Dlf-ENSIONS 

WING AREA SW » 2690.00 SQ.FT. 

WING SPAN BW » 78.056 FT. 

M.A.C. CW = 39.560 FT. 

BOOY LENGTH LB - 1390.3 IN. 





ALTITUDE (FT.) 






300000.0 


350000.0 


400000.0 


450000.0 


500000.0 


550000.0 


600000.0 


ALPHA (OEG) 


A 


8 


C 





E 


F 


G 






HIGH ALTITU 


EC PITCHING 


MOMENT CO 






20.000 


-0.00600 


-0.05300 


-0.10200 


-0.12821 


-0.13313 


-0.14126 


-0.14175 


25.000 


-0.00800 


-0.07087 


-0.13640 


-0.17145 


-0.18471 


-0.18891 


-0.18956 


30.000 


-0.01500 


-0.09200 


-0.17226 


-0.21519 


-0.23143 


-0.23657 


-0.23737 


35.000 


-0.02600 


-0.11120 


-0.20002 


-0.24752 


-0.26549 


-0.27118 


-0.27206 


40.000 


-0.04100 


-0.13302 


-0.22893 


-0.28024 


-0.29965 


-0.30579 


-0.30674 


45.000 


-0.06100 


-0.15384 


-0.25062 


-0.30239 


-0.32197 


-0.32817 


' -0.32913 


50.000 


-0.08200 


-0.17532 


-0.27251 


-0.32464 


-0.34433 


-0.35056 


-0.35152 



ENGINEER 
DATE ; 



NASA 



FIGURE 4.1.1.3-6 
BASIC PTTrMTNH MOMENT COEFFICIENT 



4.1.1.3-12 



750000 



^_/ 



c r 



-GH-CCC. C IM 



wj^ Rockwell International 

Space Division 



MACH NUMBER 



DELE CDEGD 

-50 -25 25 

i I I I | I I M | I I M | 



LU 

a 



-.3 




5 10 

ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XQ = FS 1076.7 IN. 

OR YO » BL 0.0 IN. 

MGt£NT REFERENCE ZO » WL 375.0 IN. 



REFERENCE D[f£NSI0N5 
WING AREA SW - 2690.00 SQ.FT. 
UING SPAN 8W = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

8COY LENGTH LB " 1290-3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


B 


C 





E 


F 


G 


H 






ELEVON 


PITCHING M 


Of-CNT INCRE 


-ent 






-40.000 


0.18130 


0.18430 


0.16800 


0.16100 


0. 16400 


0.17270 


0.19590 


. 22280 


-35.000 


0.18280 


0.18680 


0.16500 


0.16200 


0.16600 


0.18380 


0.21010 


0.23390 


-30.000 


0.17970 


0.18460 


0.16400 


0.16510 


0.16800 


0.19240 


0.21920 


0.23140 


-25.000 


. 1 7570 


0.18030 


0.16200 


. 16500 


0.16900 


0.19540 


0.21670 


0.20810 


-20 . 000 


0.16910 


0.17220 


0.15800 


0.16100 


0.16800 


0.18030 


0.18580 


0.17720 


-15.000 


0.13970 


0.14000 


0.13500 


0.13300 


0.13800 


0.14430 


0.14380 


0.13400 


-10.000 


0.09420 


. 09500 


0.09000 


0.09370 


0.09600 


0.09700 


. 09570 


0.09000 


-5.000 


0.04810 


0.04910 


0.04600 


0.04500 


. 04660 


0.04750 


0.04760 


0.04510 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.04300 


-0.04410 


-0.04410 


-0.04510 


-0.04510 


-0.04500 


-0.05010 


-0.04150 


10.000 


-0 . 08750 


-0 . 09220 


-0.08900 


-0 . 08960 


-0.09220 


-0.09470 


-0.09920 


-0 . 06660 


15.000 


-0.12950 


-0.13870 


-0.13500 


-0.13570 


-0.13870 


-0.14100 


-0.14530 


-0.12860 


20.000 


-0.17300 


-0.18430 


-0.1B000 


-0.17970 


-0. 18430 


-0.19040 


-0. 19440 


-0 . 1 7420 



ENGINEER P<^> 
DATE. 3/13/2. it. 



ELEVON 



FIGURE 4.1.1.3- 7 

PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-13 



sr 7i: -SK-coeo im 



#i» 



Rockwell International 

Space Division 



MACH NUMBER = 0.400 

■3 r i i u I | | | i I I I i I I I I i l I I i l i I I 



OELE CDEGO 

-50 -25 



UJ 

2: 
u 

Q 




-.3 



5 10 
ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - 8L 0.0 IN. 

MOMENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SU - 2690.00 5Q.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 
BCOY LENGTH LB - 1290.3 IN. 



DELE (PEG) 



-HO. 000 

-35.000 

-30 . 000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15-000 

20.000 



ALPHA (DEG) 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
D 



0.000 
E 



15.000 
F 



20.000 
G 



ELEVON PITCHING MOt-gNT INCREMENT 



25.000 
H 



0.16130 

0.18280 

0.17970 

0.17570 

0.16910 

0.13970 

0.09420 

0.04810 

0.0 

-0.04300 

-0.08750 

-0.12950 

-0.17300 



0.18430 

0.18660 

0.18480 

0.18030 

0.17220 

0.14000 

0.09500 

0.04910 

0.0 

-0.04410 

-0.09220 

-0.13870 

-0. 18430 



0.16800 

0.16600 

0.16400 

Q. 16200 

0.158C0 

. 1 3500 

0.09000 

0.04600 

0.0 

-0.04410 

-0.08900 

-0.13500 

-0.18000 



0.16100 

0.16200 

0.16510 

0.16500 

0.16100 

0.13300 

0.09370 

0.04500 

0.0 

-0.04510 

-0 . 08960 

-0.13570 

-0.17970 



0, 

0. 















-0 

-0 

-0 

-0 



16400 
16600 
16B0O 
16900 
16800 
13800 
09600 
04560 


04510 
.09220 
.13870 
.18430 





















-0 

-0 

-0 

-0 



.17270 
.18380 
.19240 
.19540 
.18030 
.14430 
.09700 
.04760 
.0 

.04500 

.09470 

.14100 

19040 



0.19590 
0.21010 
0.21920 
0.21670 
0.18580 
0.14380 
. 09570 
0.04760 
0.0 

-0.05010 
-0.09920 
-0. 14580 
-0. 19440 



0.22280 

0.23390 

0.23140 

0.20810 

0.17720 

0. 13400 

. 09000 

0.04510 

0.0 

-0.04150 

-0 . C8660 

-0. 12860 

-0.17420 



ENGINEER £-C£_ 
OATE £7l37-?f 



ELEVON 



FIGURE 4.1.1.3-8 

pttphtnp; MHMFNT COEFFICIENT INCREMENT 



4.1.1. 3-U 



U"7L-SH -ocec JM 



#1% 



Rockwell International 

Space Division 

L 



MACH NUMBER 
• 3 < I I I l I i l I 



u 

z: 

8 



.1 



.0 



-.] 



-.a 



0.600 

i l I I 



-50 



DELE 

-25 



CDEG'J 
o 



25 



I I I 



illl 




! i I I | I I 



| l I II 



I I I i I I i I 



Illl 



. 3 1 M I I I I 1 I I I I M J I I I M I I I I I I i 1.1 1 1 1 1 I i ll I I I I I.I 1 

'-20 -15 -10 -5 5 10 15 20 25 



ALPHA CDEGD 



20 



COM 7 1 CURAT ION 




BASELIh£ OR81TER VEHICLE 


REFERENCE OI^NSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WINS SPAN BW » 78.056 


FT. 


MCtCNT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 



ENGIt^lER j9<2> 



ELEVON 



FIGURE 
PITCHING 



4.1. 1.3- 

MGMENT 



COEFFICIENT INCREMENT 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEVON 


PITCHING M 


OTENT INCRE 


-ENT 






-40.000 


0.16140 


0.16610 


0.15350 


0.15100 


0.15950 


0.15400 


0. 17610 


. 1 3600 


-35.000 


0.16700 


0.17190 


0.15580 


0.15210 


0. 16000 


0.15750 


0.17560 


0.14770 


-30.000 


0.16950 


0.17150 


0.15500 


0.15300 


0.16000 


0. 16150 


0. 17560 


0.15740 


-25.000 


0.16750 


0.16550 


0.15300 


0.15300 


0.15920 


0.16450 


0.17210 


0.16090 


-20.000 


0.15890 


0.15330 


0.14700 


0.14700 


0.15400 


0.16400 


0.16350 


0.15130 


-15.000 


0.13860 


0.13150 


0.12900 


0.12950 


0.13620 


0.14000 


0.13860 


0. 12540 


-10.000 


0.09750 


0.09650 


0.09350 


. 09400 


0.09600 


. 09590 


0.09240 


' 0.08400 


-5.000 


. 04870 


0.05000 


0.04750 


. 04800 


. 04900 


. 04600 


. 04700 


. 04200 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0 . 04370 


-0 . 04800 


-0.04700 


-0.04800 


-0.04700 


-0.04800 


-0.04H70 


-0 . 04 1 80 


10.000 


-0 . 09240 


-0.09550 


-0 . 09450 


-0 . 09700 


-0.10200 


-0 . 09600 


-0.09190 


-0.08310 


15.000 


-0.13550 


-0.14300 


-0. 14000 


-0.14700 


-0.15300 


-0.13800 


-0.13760 


-0. 11940 


20.000 


-0.15990 


-0.17900 


-0.18100 


-0.18600 


-0.20400 


-0 . 1 7800 


-0.16830 


-0. I u 920 



4.1.1.3-15 



^ 



Rockwell International 

Space Division 



MACH NUMBER 
• 3 | I ! i I I I I I I 



0.800 



DELE CDEG3 
50 -2 5 25 

I I I I i i i i I I ; I i 



u 
u 

Q 




-20 



ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO - FS 107S.7 IN. 
OR YO - BL 0.0 IN. 

MC*£NT REFERENCE ZO - WL 375.0 IN. 



REFERENCE OlfENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BOOY LENGTH LB ° 1290.3 IN. 



OELE (DEG) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (PEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



20 . 000 
G 



25.000 
H 



ELEVON PITCHING MOMENT INCREMENT 



0.16840 

0.16650 

0.16370 

0. 16030 

0.15590 

. 1H490 

0.11310 

0.05380 

0.0 

-0. 04 080 

-0 . 08450 

-0.11870 

-0. 14140 



0.20700 

0.20100 

0.19000 

0.17150 

0.15250 

0.13100 

. 1 0000 

0.05800 

0.0 

-0.05600 

-0.10320 

-0.14650 

-0.18030 



0.18750 

0.17950 

0.16950 

0.15560 

0.13600 

. 1 1420 

0.08700 

0.05300 

0.0 

-0.05250 

-0.10400 

-0.15000 

-0.19100 



0.17180 

0.16430 

0.15600 

0. 14600 

0.13200 

0.11230 

0.06800 

0.05580 

0.0 

-0.05600 

-0.11300 

-0.1 5980 

-0.20200 



. 1 7800 

0.16400 

0.15000 

0.13500 

0.12000 

. 1 0640 

0.08950 

0.05300 

0.0 

-0 . 04800 

-0.10250 

-0.15000 

-0. 18610 



0. 14750 

0. 14080 

0.13400 

0.12600 

0.11800 

0.10880 

0.09420 

. 05000 

0.0 

-0.05400 

-0.10800 

-0. 14950 

-0.18150 



0.10360 

0.10980 

0.11500 

0.11850 

0.11940 

0.10970 

0.08700 

0.04480 

0.0 

-0 . 04900 

-0.09200 

-0.12760 

-0.15080 



0.08590 

. 09720 

0.10760 

0.11550 

. 1 1 790 

0.10520 

0.07950 

. 03970 

0.0 

-0 . 03990 

-0.07900 

-0.10900 

-0.12950 



ENGINEER &&> 
OATE__3//3/3l£. 



FIGURE 4.1.1.3-10 
n rvnN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-16 



£D72 -Sii-GCC C 1 M 



* 



Rockwell International 

Space Division 



MACH NUMBER 
• 3 ' i l II i i i i i i i i i 



0.900 



DELE CDEG] 

-25 25 

I I I I 



LU 




5 10 

ALPHA COEGD 



CONFIGURATION 


BASEL INE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO =■ BL 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MOMENT REFERENCE ZO - ML 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 



DELE (DEG) 



-MO. 000 

-35.000 

-30.000 

-25.000 

-20 . 000 

-15.000 

- 1 . 000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (DEG) 



-10.000 
A 



-5.000 
8 



0.0 

c 



5.000 
D 



10.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



ELEVON PITCHING MOMENT INCREMENT 



0.17100 

0.16690 

0.16350 

0.15780 

0.15180 

0.13920 

0. t 1510 

. 05760 

0.0 

-0.04290 

-0.08120 

-0.11550 

-0.14930 



0.21000 

0.20770 

0.20100 

0.18770 

0.15800 

0.14150 

0.10600 

. 05800 

0.0 

-0.05400 

-0 . 09000 

-0.12900 

-0.16400 



0.19380 

0.19280 

0.18700 

0.17580 

0.15700 

0.13230 

. 09600 

0.05150 

0.0 

-0.04800 

-0.09150 

-0.13950 

-0.18600 



0.18600 

0.18000 

0.17000 

0.15250 

0.13200 

0.10300 

. 07000 

0.03200 

0.0 

-0.05100 

-0.11100 

-0.15400 

-0.21200 



0.14150 

0.13250 

0.12350 

0.11200 

0.10000 

0.08420 

. 06300 

0.03800 

0.0 

-0 . 05000 

-0.11 300 

-0.16350 

-0.20200 



0.11200 

0.11000 

0.10800 

0.10420 

0.09820 

0.08900 

0.07500 

0.04400 

0.0 

-0.05800 

-0.11400 

-0.15400 

-0.18200 



0.08990 
0.09360 
0.09680 
. 09950 
0.10070 
0.09880 
. 08430 
0.04640 
0.0 

-0 . 04500 
-0 . 09030 
-0.12410 
-0. 14420 



. 07730 

. 08650 

0.09530 

0. 10150 

0. 10370 

0.09680 

0.07670 

0.04 100 

0.0 

-0 . 03990 

-0.08CC0 

-0 . 1 0940 

-0. 12900 



ENGINEER A<^> 
OATE.. %JS/L3/.2£ 



ELEVON 



FIGURE 4.1.1.3-11 

PITCHING MOMENT COLTF I C I ENT INCREMENT 



4.1.1.3-17 



SL 72-SH-OCCC 1 M 




Rockwell International 

Space Division 



MACH NUMBER = 0.950 

■ 3 i i I l l T l i I l I i ll I I I I i i I I 



DELE CDEG) 

•50 -25 25 

f i I i i | I I I I | i i I I 



Ul 

21 

Q 



-.2 




5 10 

ALPHA CDEG) 



CONFIGURATION 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO » FS 1076.7 IN. 
OR YO - 0L 0.0 IN. 

MOENT REFERENCE ZO - UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW * 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW = 39.560 FT. 

BODY LENGTH LB ■ 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OGLE (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEVON 


PITCHING M 


Ct£NT INCRE1 


^£NT 






-HO. 000 


0.17350 


0.21900 


0.21000 


0.20900 


0.15900 


. 1 3000 


0.09230 


0.08070 


-35.000 


0.16870 


0.21400 


0.20900 


0.20500 


0.15500 


0.12500 


0.09450 


0.09050 


-30.000 


0.15340 


0.20800 


0.20500 


0.19700 


0.15000 


0.12000 


. 09670 


0.09820 


-25 . 000 


0.15810 


0.19830 


0.19950 


0.18450 


0.14150 


. 1 1 300 


0.09840 


. 1 0290 


-20.000 


0.15170 


0.18250 


0. 18800 


0.16400 


0.12700 


0. 10400 


0.10010 


. 1 0360 


-15.000 


0.14340 


0.16150 


0.16550 


0.13500 


0.10550 


0.09400 


0.09820 


. 09970 


-10.000 


0.11500 


0.12800 


0.12850 


0.09700 


0.07500 


. 07500 


0.08290 


0.07740 


-5.000 


0.06000 


0.06900 


0.06500 


. 05000 


0.04200 


0.04000 


. 05000 


0. 04 190 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.03740 


-0.04000 


-0.03800 


-0.04800 


-0.05000 


-0.05300 


-0.04700 


-0.04040 


to. 000 


-0.07890 


-0.07300 


-0.08200 


-0.10400 


-0.11000 


-0 . ! 0400 


-0.08840 


-0.07940 


15.000 


-0.11780 


-0. 11000 


-0.12700 


-0.16000 


-0.16400 


-0. 14900 


-0. 119S0 


-0.10830 


20.000 


-0.14870 


-0.16000 


-o.ieooo 


-0.20400 


-0.20600 


-0.17400 


-0. 1^470 


-0 . 1 2760 



ENGINEER QCO 
QrtE.2/lJU.?£- 



ELEV0N 



FIGURE 
PITCHING 



4.1.1.3-12 

MOMENT PflFFFIC IENT INCREMENT 



4.1.1.3-18 



KS 



ZZ 72-SH-CCGC 1M 



#i* 



Rockwell International 

Space Division 



L 



MACH NUMBER 



0.980 



UJ 

2: 

Q 




ALPHA CDEGD 



CONFIGURATION 



BASELINE 0R81TER VEHICLE 

CENTER OF GRAVITY XO =■ FS 1075.7 IN. 

OR YO =■ BL 0.0 IN. 

MOMENT REFERENCE ZO « W_ 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW » 78.055 FT. 
11. A. C. CW = 39.560 FT. 

BODY LENGTH L9 = 1290.3 IN. 





























ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEVCN 


PITCHING M 


CMENT INCRE 


r-ENT 






-40.000 


0.17369 


0.20695 


0.20433 


0.20888 


0.16744 


0.13949 


. 09485 


0.08346 


-35.000 


0.16903 


0.20345 


0.20203 


0.20354 


0.16549 


0.13323 


. 0S649 


0.09296 


-30.000 


0.16309 


0.19725 


0.19713 


0.19505 


0.15146 


0.12677 


. 09830 


0.09991 


-25.000 


0.15729 


0.18807 


0.19075 


0.18355 


0.15288 


0.11848 


0.09943 


0.10373 


-20.000 


0.14911 


0.17386 


0.17897 


0.16520 


0.13562 


0.10790 


0.09961 


0.10335 


-15. COO 


0.14008 


0.15440 


0.15744 


0.13347 


0.11292 


0.09614 


0.09574 


0.09656 


-10.000 


0.11155 


0.12366 


0.12175 


0.09951 


0.0802! 


0.07435 


0.08145 


0.07409 


-5.000 


0.05822 


0.06297 


0.06064 


0.05408 


0.04347 


. 03935 


. 05058 


0.04010 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.03789 


-0.04001 


-0.03891 


-0.0470! 


-0 . 05000 


-0.05119 


-0.04647 


-0.04065 


10.000 


-0 . 07S53 


-0 . 07649 


-0.08434 


-0 . 1 0270 


-0 . 1 0820 


-0.10164 


-0 . 08766 


-0.07901 


15.000 


-0. 11904 


-0.11483 


-0.12936 


-0. 15744 


-0.15970 


-0.14508 


-0.11891 


-0.10764 


20 . 000 


-0. 14834 


-0. 16150 


-0.17872 


-0.19884 


-0.I99S9 


-0.17323 


-0.14299 


-0.12563 



JEnGI 
lOATE 



i-EER ^Co 



ELEVON 



FIGURE 

PITCHING 



4. 1.1.3- 

MOMENT 



■ 13 

COEFFICIENT 



INCREMENT 



4.1.1.3-19 



c ■?:.--S:-;-ccec jm 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.050 



-50 



DELE CDEGD 

-25 

"tti i i i i | i i r 



25 



.2 



UJ 

a 
a 



-.2 



rrn in m 



TT 




. 3 I1 I I I I I I I I I I I I I I I I I I I I I I I I I I I I I 1 I I ! I I I I I 'I 1 I 

-20 -15 -10 -5 5 10 15 20' 

ALPHA CDEG) 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DICCNSIONS 


CENTER OF GRAVITY XO » FS 1075.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


UING SPAN BW - 78.056 FT. 


MGftNT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB * 1290.3 IN. 



ENGINEER &&> 
OATE. 



FIGURE 4.1.1.3-14 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-20 



30 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


£5 . 000 


DELE (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEVON 


PITCHING MOMENT iNCRE 


-£NT 






-40.000 


0.17250 


0.17450 


0.18600 


0.18650 


. 1 7700 


0. 15450 


0.10430 


. 0S280 


-35.000 


0.16730 


0.16880 


0.17950 


0.17950 


. 1 7600 


0. 14800 


0.10460 


0.0S910 


-30.000 


0.16100 


0.15250 


0.17100 


0.17050 


0.17000 


0.14000 


0.10430 


0.10380 


-25.000 


0.15270 


0.15470 


0.16100 


0.16000 


0.15800 


0.13150 


0.10210 


0.10560 


-20.000 


0. 14240 


0. 14500 


0.14800 


0.14550 


. 1 3970 


0.11750 


. 09780 


0. 10180 


-15.000 


0.12970 


0.12970 


0.13100 


0.12200 


0.11450 


. 09750 


. 09000 


. 09800 


-10.000 


0. 10080 


. 1 0750 


0.10100 


0.09200 


0.08400 


0.07160 


0.07520 


. 06420 


-5.000 


0.05290 


0.04000 


0.04650 


. 04950 


0.04300 


. 03900 


0.04640 


. 03390 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-o.onmo 


-0 . 04400 


-0.04550 


-0 . 04550 


-0.05000 


-0.04800 


-0.04390 


-0.04090 


10.000 


-0 . 07820 


-0 . 09300 


-0.09600 


-0.10200 


-0.1 0400 


-0 . 09800 


-0 . C8630 


-0.07820 


15.000 


-0.12110 


-0.13600 


-0.14300 


-0.15050 


-0.14600 


-0.13500 


-0. 1 1810 


-0.10610 


20.000 


-0.14750 


-0.15600 


-0.17800 


-0.18500 


-0.18000 


-0.17500 


-0.13840 


-0.1 1990 



ft: 



Sf-:-r-< 



>' r 



M 



0$ 



Rockwell International 

Space Division 



MACH NUMBER 



1. 100 



DELE CDEG) 

50 -25 



UJ 

j: 
u 

Q 



-.1 




- 7U. I I I I I I I I I I I I I I i i i i I i 
-20 -15 -10 -5 



5 10 

ALPHA CDEGD 



CONFIGURATION 



BASEL INC CRBITER VEHICLE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

CR YO ■ BL 0.0 IN. 

MGMENT REFERENCE 20 = U_ 375.0 IN. 



REFERENCE OI PENSIONS 
WING AREA SW = 2690.00 SO. FT. 
WING SPAN SW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 



CELE IC€G) 



-40.000 

-35.000 

-30.000 

-25.000 

-20.000 

-i5.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



-10.000 
A 



-5.000 
B 



ALPHA (OEG) 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



0.17110 

0.16330 

0. 15560 

0.14730 

0.13850 

0.12570 

0.10170 

0.05080 

0.0 

-0.03870 

-0 . 07700 

-0.11600 

-0.14500 



ENGINEER £*2? 



0.17820 

0.16940 

0.15960 

0.14S90 

0.14000 

0.12520 

0.09500 

0.04630 

0.0 

-0 . 04000 

-0.08700 

-0. 13000 

-0.16400 



ELEVON PITCH I NO HOHENT INCREMENT 



20.000 



25.000 
H 



18020 
1 7290 
16470 
15440 
14050 
. 12230 
.08550 
0.04200 
0.0 
-0 . 04000 
-0 . 08600 
-0,12550 
-0. 16450 



0.16150 

0.15550 

0.14700 

. 1 3700 

0.12400 

0.11250 

. 08300 

0.03850 

0.0 

-0.04000 

-0.09400 

-0 . 1 3450 

-0 . 1 7000 



0.15500 

0.15100 

0.14600 

. 1 3800 

0.12500 

. 1 0200 

. 07200 

0.03600 

0.0 

-0 . 04600 

-0.10000 

-0.14750 

-0.18100 





















-0 

-0 

-0 

-0 



.13400 
.13200 
.12900 
.12200 
.11000 
.09200 
. 06900 
.03600 
.0 

. 04200 

. 09200 

.13350 

16200 



FIGURE 4.1.1.3-15 

ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



0. 1 1430 
0.1 1260 
0.10940 
0.10370 
0.C9440 
0.08210 
. 06270 
. 03700 
0.0 

-0.04600 
-0.08400 
-0. 11400 
-0 . 1 3550 



0.1 0420 
0.10760 
1 0650 
10450 
. 09800 
. 08350 
.06150 
. 03670 
.0 

. 03770 
-0.07330 
-0. 1C540 
-0.12330 



0. 

0. 
0. 
0. 
0. 
0. 
0. 
-0. 



4.1.1.3-21 



SD72 -5 



■C ;t?C 



4* 



Rockwell international 

Space Division 



NUMBER 



UJ 

r 
o 

Q 




5 10 
ALPHA CDEG) 



CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1075.7 IN. 

or yo = a. o.o in. 

[OhENT REFERENCE 20 - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN BW - 79.056 FT. 
M.A.C. CW ' 39.550 FT. 

BCOY LENGTH LB = 1890.3 IN. 



DELE 1DEG) 



-40.00Q 
-35.000 
-30.000 

-as. ooo 

-20 . 000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

1 . 000 

15.000 

20.000 



ENGINEER &&> 



ELEVON 



FIGURE 4.1.1.3-16 

PITCHING MOMENT COEFFICIENT INCREMENT 









ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


A 


8 


C 


O 


E 


F 


G 


H 






ELEVON 


PITCHING M 


DMENT [NCRE 


*ENT 






0.16880 


0.17500 


0.17290 


0.16500 


0.14910 


0.13020 


0.12060 


0.11340 


0.16110 


0.16820 


0.16360 


0.15360 


0.14030 


0.12300 


0. 11540 


0.11050 


0.15280 


0.15940 


0.15280 


0.14120 


0.12990 


0.11470 


0.10910 


0.10510 


0.14200 


0. 14810 


0.13940 


0.12730 


0.11610 


. 1 0390 


. 1 0030 


0.09820 


0.I29I0 


0.12S60 


0.12000 


0.11130 


0.09870 


0.09200 


0.09000 


. 08830 


0.11020 


0.10610 


0.09540 


0.09040 


. 07870 


0-07610 


0.07400 


. 07460 


0.09460 


0.07400 


0.06690 


. 06330 


. 05570 


0.05570 


0.05570 


. 05570 


0.04280 


0.03620 


0.03370 


. 03370 


0.02860 


0.03110 


0.03110 


0.03110 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


-0.03770 


-0.03750 


-0.03500 


-0 . 03650 


-0.04150 


-0.04000 


-0 . 03880 


-0.03880 


-0.07750 


-0.07500 


-0.07750 


-0.08350 


-0.09000 


-0.08700 


-0 . 080 1 


-0 . 07600 


-0.11100 


-0.11500 


-0.11450 


-0.12300 


-0.13400 


-0.12800 


-0.11170 


-0.10290 


-0. 141H0 


-0.14700 


-0.15200 


-0.16700 


-0.16950 


-0.16000 


-0. 13010 


-0.11690 



4.1.1.3-22 



L 



-CCCC 1M 




Rockwell International 

Space Division 




ALPHA CDEGD 



CGt^IGURATlON 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2590.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOhtNT REFERENCE ZO * W. 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BCOY LENGTH LB * 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELE <DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






ELEVON 


PITCHING M 


OENT INCRE 


MENT 






-MO. 000 


0.15300 


0.17500 


0.16400 


0.16000 


0.11800 


0.10200 


0.12040 


0.11480 


-35.000 


o.i46io 


0.I5S00 


0.15000 


0.14750 


0.11600 


0.10390 


0.11200 


0.10800 


-30.000 


0.13770 


0.15350 


0.13400 


0.13200 


0.1 1180 


0.10050 


0.10310 


0.10010 


-85.000 


0.12730 


. 1 3650 


0.11750 


0.11450 


0.10190 


0.09350 


0.09270 


0.09120 


-20 . 000 


0.11390 


0.11570 


. 09800 


. 09600 


0.08950 


0.08250 


0.08070 


0.C8130 


-15.000 


. 09490 


0.08700 


0.07750 


0.07450 


0.07200 


. 06750 


0.05880 


0.06880 


- 1 . 000 


. 07050 


0.06100 


. 05570 


0.05350 


. 05200 


0.04960 


0.05290 


0.05340 


-5.000 


0.03800 


0.03000 


. 02700 


0.02850 


. 02800 


. 02750 


. 0300C 


0.03000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.03G00 


-0.03210 


-0.03100 


-0 . 03200 


-0.03800 


-0.03650 


-0 . 03350 


-0.03300 


10.000 


-0 . 05990 


-0.C6350 


-0 . 06350 


-0.06700 


-0.07550 


-0 . 07450 


-0.06BO0 


-0.07050 


15.000 


. -0.09040 


-0 . 09650 


-0.10050 


-0.10770 


-0.11350 


-0.11150 


-0.09890 


-0.09990 


20 . 000 


" -0.12190 


-0.13100 


-0 . 1 3800 


-0.14850 


-0.15250 


-0. 14700 


-0.11790 


-0.11990 



ENGINEER QfO 



FIGURE 4.1.1.3-17 
ELEVCN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-23 



OOSC IM 




Rockwell International 

Space Division 



MACH NUMBER 



1.500 



DELE (DEC? 
-as o es 



3 I I I ! I I l I ! I I II ! I I I I I I I I I I 



i I | i i i i 



.1 



UJ 

n 
o 
a 



-.1 




>3 i i i i i I i i i i i i i i 

-20 -15 -10 -5 



i I I 1 1 



I I I 



I I I 



I I I ' I I I 



-fr-^r^: 



ii i i i i i 



fa: 



I I I 



I [ 1 I I I I I I 






5 10 

ALPHA CDEG) 



15 



ao 



25 



CONFIGURATION 




BASELINE CR8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 


FT. 


MOMENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW ■ 39.560 


FT. 




BOOY LENGTH LB » 1290.3 


IN. 



ENGINEER &&> 



ELEVON 



FIGURE 4.1.1.3-18 

P I TCH I NG MOMENT COEFFICIENT INCREMENT 



4.1.1.3-24 



30 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE <C€G1 


A 


B 


C 





E 


F 


G 


H 






ELEVON 


PITCHING h 


OMENT INCRE 


"ENT 






-HO . 000 


0.15421 


0.13212 


0.12756 


0.11215 


0.11979 


0.11453 


0.10569 


0.10472 


-35.000 


0.14469 


0.12319 


0.11837 


0.10562 


0.10797 


. 1 0348 


0.09438 


0.09210 


-30 . 000 


0.13203 


. 1 1265 


0.10759 


0.09863 


0.09303 


0.09099 


0.09438 


0.08153 


-25.000 


0.11574 


0.09920 


0.09389 


0.08853 


0.08000 


0.07773 


0.07395 


0.07148 


-20.000 


0.09231 


0.08334 


0.07965 


0.07481 


0.07118 


0.06815 


0.06697 


0.06526 


-15.000 


. 07092 


0.06755 


0.06290 


0.06054 


0.05560 


0.05448 


0.05381 


0.05297 


-10.000 


0.04979 


0.04765 


0.04415 


0.04472 


0.03929 


0.03781 


0.03754 


. 03727 


-5.000 


0.02291 


. 0234H 


0.02215 


0.02231 


0.02133 


0.02165 


0.02038 


. 02090 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.02339 


-0 . 02445 


-0 . 02427 


-0 . 02375 


-0 . 02670 


-0.02600 


-0.02710 


-0.03059 


10.000 


-0 . 04486 


-0 . 04927 


-0.04797 


-0.05121 


-0 . 05687 


-0 . 06024 


-0.06954 


-0 . 07489 


15.000 


-0.06716 


-0.07289 


-0.07380 


-0.07S64 


-0.08768 


-0.10070 


-0.11221 


-0.12125 


20 . 000 


-0.08776 


-0.09437 


-0. 10163 


-0.11418 


-0.12088 


-0.13823 


-0.15245 


-0. 16406 



L72 



3! 



oa c im 



# 



Rockwell International 

Space Division 



MACH NUMBER 



2.000 



UJ 



-.3 



TTT 



I I I I 



I I i i i i I i i i i I i i ! i i ii i i i i I n — rrr 



-U_!_L 



iiii. 




-Li. I .1- 



.1 i LI 



DELE CDEG3 

-5 -25 25 

| II 11 | II I I | I I ! I | 

i i i I i i ii — m~ 



_1_LJ_L 



r=^[ 



I I U _ 



I I I I 



-20 



-15 



-10 



-5 



5 
ALPHA 



10 

CDEG) 



15 



2rf 



25 



30 



35 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS I07S.7 IN. 


WING AREA SW * 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW « 78.056 FT. 


MOMENT REFERENCE ZO » UL 375.0 IN. 


M.A.C. CU ' 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 





ALPHA (DEG) 




-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30.000 


CO.E (DEG) 


A 


B 


C 





E 


F 


G 


H 


I 








ELEVCN PITC 


HING MOMENT 


INCREf-ENT 








-HO . 000 


0.10100 


0.09010 


0.08110 


. 06000 


0.06600 


0.06950 


0.07160 


. 07530 


0.08200 


-35.000 


0.09210 


. 08400 


. 07500 


. 05900 


. 06300 


0.06700 


0.07000 


. 07070 


. 07600 


-30 . 000 


. 08320 


0.07700 


0.07100 


0.05700 


. 05900 


. 06300 


. 06700 


. 06600 


0.07100 


-25 . 000 


0.07240 


0.06800 


0.05400 


0.05300 


0.05400 


. 05800 


0.05900 


. 05970 


. 06500 


-20.000 


0.06170 


. 05800 


. 05600 


0.04700 


. 04750 


. 05000 


. 05200 


. 05330 


. 05750 


-15.000 


0.04810 


0.04700 


. 04600 


0.03800 


. 03800 


0.04100 


. 04300 


. 04500 


0.04900 


-10.000 


0.03440 


. 03200 


. 03200 


. 02700 


. 02700 


0.02900 


0.03100 


. 03250 


0.03700 


-5.000 


0.01720 


0.01600 


0.01600 


0.01400 


0.01400 


0.01500 


0.01500 


0.01700 


0.02100 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01680 


-0.01700 


-0.01600 


-0.01500 


-0.01600 


-0.01900 


-0.01800 


-0.02150 


-0.02500 


10.000 


-0.03070 


-0.03220 


-0.03100 


-0.03100 


-0.03300 


-0.03600 


-0.04200 


-0.04630 


-0.05400 


15.000 


-0.0H530 


-0.04680 


-0 . 04500 


-0 . 04900 


-0.05400 


-0.06000 


-0 . 06700 


-0.07600 


-0.08500 


£0 . 000 


-0 . 05540 


-0.05790 


-0 . 05900 


-0 . 07900 


-0 . 07700 


-0 . 08600 


-0. 10000 


-0.10570 


-0. 1 1400 



|EM31NEER &ZC 
' DATE. J?^Z?!^- 



F1GURE 4.1.1.3- 19 

ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 

4.1.1.3-25 



.:.) 



u- 



M 



#J> 



Rockwell International 

Space Division 



MACH NUMBER = 3.000 

■ 3 " I I i I | | | M ! I t i 



DELE CDEGD 

-50 -25 25 

I I I ! I 



iii m 



ui 
o 

Q 



-.1 



-.3 



i> I 1 




I I 1 I I 1 II 



i I ! ! I I 



i^^^^jgc^^r^^^g^sr^S^Mj^, 






TTTT 



I I I I I I I I I I I I I I I I L_LJ-J_JL_L_1 



^gg|g=g^4 






1.1.1.. 1 .1— I 




I I I I I I 



I I I I 



-20 



-10 



5 10 

ALPHA CDEG) 



15 



20 



25 



CONFIGURATION 


BASELINE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OP GRAVITY XO » FS 1076.7 IN. 


MING AREA SW » 26S0.00 SQ.FT. 


OR Y0 - BL 0.0 IN. 


WING SPAN BU - 78.056 FT. 


MOtCNT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 



ENGINEER fe*^ 



ELEVCN 



FIGURE 4.1.1.3-20 

PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-26 



30 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 





E 


F 


G 


H 






ELEVON 


PITCHING M 


OMENT INCBE 


*ENT 






-HO. 000 


0.05700 


. 0H920 


0.03850 


. 03650 


. 03750 


0.04210 


. 04700 


0.05420 


-35.000 


0.05546 


0.04S70 


0.03570 


0.03370 


. 03570 


. 03930 


. 04370 


0.05090 


-30.000 


0.05160 


0.04430 


0.03130 


0.03030 


0.03300 


0.03510 


0.04000 


0.04710 


-25.000 


0.04610 


0.03930 


0.02730 


0.02630 


0.02930 


0.03250 


. 03600 


0.04260 


-20.000 


0.04030 


. 03400 


. 02300 


. 02400 


0.02500 


0.02900 


0.03130 


. 03730 


-15.000 


0.02980 


0.02480 


0.01780 


0.01780 


0.01977 


0.02258 


0.02520 


0.03050 


-10.000 


0.01590 


0.01420 


0.01220 


0.01220 


0.01400 


0.01620 


0.01780 


0.02200 


-5.000 


0.00820 


0.00740 


0.00640 


0.00640 


0.00740 


0.00870 


0.00950 


0.01180 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00712 


-0.00712 


-0.00712 


-0.00812 


-0.01020 


-0.01200 


-0.01400 


-0.01750 


10.000 


-0.01630 


-0.01630 


-0.01630 


-0.01830 


-0 . 02230 


-0.02770 


-0.03450 


-0.04250 


15.000 


-0.02000 


-0.02050 


-0.02550 


-0.02950 


-0 . 03650 


-0 . 04575 


-0.05550 


-0.06900 


20.000 


-0.02340 


-0.02350 


-0.03650 


-0 . 04350 


-0.05250 


-0.06550 


-0 . 07950 


-0.09400 



ST7 



cec im 




Rockwell International 

Space Division 



MACH NUMBER 



UJ 
XL 
C_> 
Q 




25 30 

ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OP GRAVITY XO « FS 1076.7 IN. 

OR YO » a. 0.0 IN. 

MOMENT REFERENCE 20 = M. 375.0 IN. 



ION 




REFERENCE DIMENSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW - 78.055 


FT. 


M.A.C. CW ■ 39.560 


FT. 


BODY LENGTH LB » 1290.3 


IN. 



ENGINEER Q^O 
DATE <?//j 









ALPHA (DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVCN PITC 


HING MOMENT 


INCREMENT 






-40.000 


0.04210 


0.04700 


0.05420 


0.06330 


0.07240 


0.08180 


0.09140 


-35.000 


0.03930 


0.C4370 


0.050SO 


0.05960 


0.06890 


0.07860 


0.08840 


-30.000 


0.03610 


0,04000 


0.04710 


0.05550 


0.06520 


0.07510 


0.08520 


-25.000 


0.03250 


0.03600 


0.04260 


0.05080 


0.06050 


0.07000 


0.07970 


-20.000 


0.02800 


0.03130 


0.03730 


0.04500 


0.05440 


. 06390 


0.07330 


-15.000 


0.02258 


0.02520 


0.03050 


0.03660 


0.04510 


. 05360 


. 06040 


-10.000 


0.01620 


0.01780 


0.02200 


0.02620 


0.03200 


0.03790 


0.04300 


-5.000 


. 00870 


0.00950 


0.01180 


0.01430 


0.01720 


0.02030 


0.02210 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01200 


-0.01400 


-0.01750 


-0.02000 


-0.02570 


-0.02750 


-0.03080 


10. COO 


-0.02770 


-0 . 03450 


-0.04250 


-0.04900 


-0.05420 


-0 . 06020 


-0 . C6660 


15.000 


-0 . 04575 


-0 . 05550 


-0.06900 


-0.07990 


-0.08190 


-0.08390 


-0.08670 


20 . 000 


-0.06550 


-0 . 07950 


-0.09400 


-0.10750 


-0.10800 


-0.10860 


-0.11220 



FIGURE 4.1.1.3-21 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-27 



M 



Rockwell International 

Space Division 



MACH NUMBER 



4.000 



DELE CDEGJ 

50 -25 



2: 

8 



-.2 




- -3 ri iii i i i i i i i i 

'-20 



5 10 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DINtNSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 8690.00 SQ.FT. 


OR YO «= 8L 0.0 IN. 


WING SPAN BW =» 78.056 FT. 


MCtCNT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BOOY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELE (C€G) 


A 


B 


C 





E 


F 


G 


H 






ELEVON 


PITCHING M 


OMENT [NCRE 


fCNT 






-HO. 000 


0.05750 


0.04230 


0.03530 


0.02930 


0.02830 


0.03170 


. 03500 


. 04260 


-35.000 


0.05380 


0.03760 


0.03160 


0.02660 


0.02560 


0.02910 


0.03300 


0.04030 


-30.000 


0.05040 


. 03320 


0.02820 


. 02320 


C . 02320 


0.02660 


0.03100 


0.03770 


-25.000 


0.04310 


. 02700 


0.02300 


0.01900 


. 02000 


0.02370 


0.02840 


0.03475 


-20.000 


0.03700 


0.02200 


0.01800 


0.01600 


0.01700 


0.02050 


. 02530 


0.03110 


-15.000 


0.02720 


0.01640 


0.01340 


0.01140 


0.01340 


0.01700 


0.02150 


0.02675 


-10.000 


0.01590 


0.01030 


0.00730 


0.00630 


0.00930 


0.01275 


0.01600 


. 02020 


-5.000 


0.0C570 


0.00470 


0.00270 


0.00170 


. 004 70 


. 00700 


0.00900 


0.01130 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00210 


-0.00210 


-0.00330 


-0.00520 


-0.00700 


-0.01000 


-0.01200 


-0.01650 


10.000 


-0.00550 


-0.00550 


-0.00780 


-0.01170 


-0.01680 


-0.02270 


-0.03000 


-0.03650 


15.000 


-0.01310 


-0.01310 


-0.01610 


-0.02140 


-0.02990 


-0.04000 


-0.05250 


-0.06200 


20.000 


-0 . 02050 


-0 . 02C60 


-0.02600 


-0 . 03470 


-0.04700 


-0 .'06250 


-0.07900 


-0.09450 



ENGINEER &&? 

0ATE..gx£i»Z5?Z 



FIGURE 4.1.1.3-22 
ELEVGN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-28 



S;; 7 ? 



;-!-ccec IM 



4* 



Rockwell International 

Spaca CivtsJon 



MACH NUMBER 
• 3 < I l l l 



4.000 



-50 



DELE 

-25 



CDEGD 
o 



25 



u 

u 
a 



-.2 



TTTT 



I I I I 




J_L 



_L_L__L 



_1_L_L 



_LJ_L 



I I I I 



T~T" FT 



I I I I | 
I I I I 



J I I J_ 



r ? i" 



_^_ ^_^ .<_. 



TTT - r 



I I I 



[111 



10 15 20 25 30 

ALPHA CDEG) 



i*0 



45 



50 



a*FIGURATICN 




BASELINE ORBITER VEHICLE 


REFERENCE OI^CNSICNS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MGttNT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVCN PITCHING MCf-ENT 


INCRE^NT 






-HO. 000 


0.03170 


0.03500 


0.04250 


0.05180 


0.06300 


0.07520 


0.06800 


-35.000 


0.02910 


0.03300 


0.04030 


. 04920 


0.06020 


0.07210 


0.08450 


-30 . 000 


0.02660 


0.03100 


0.03770 


0.04660 


0.05750 


0.06900 


0.08090 


-25.000 


0.02370 


0.02040 


0.03475 


0.04320 


0.05350 


0.06420 


0.07520 


-20.000 


0.02050 


0.02530 


0.03110 


0.03900 


0.04880 


0.05880 


0.06890 


-15.000 


0.01700 


0.02150 


0.02675 


0.03310 


0.04160 


0.04960 


0.05680 


-10.000 


0.01275 


0.01600 


0.02020 


0.02500 


0.03100 


0.03690 


0.04250 


-5.000 


0.00700 


0.00900 


0.01130 


0.01425 


0.01780 


0.021 30 


0.02340 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01000 


-0.01200 


-0.01650 


-0.01950 


-0.02430 


-0.02910 


-0.03300 


10.000 


-0.02270 


-0 . 03C00 


-0.03650 


-0.04350 


-0.05150 


-0.05910 


-0.06640 


15.000 


-0.04000 


-0.05250 


-0.06200 


-0.07325 


-0.08120 


-O.0882O 


-0.09380 


20 . 000 


-0 . 06250 


-0 . 07900 


-0.09450 


-0 . 1 0850 


-0.11390 


-0.11930 


-0.12420 J 



JEhGIhEER gC0 



FIGURE 4.1. 1.3- 23 
ELEVCN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-29 



SD72-SH-0C6C 1 M 



<fl 



Rockwell International 

SpaoaDtv»tco 



MACH 



NUMBER 



UJ 

r 
u 

Q 




5 10 

ALPHA CDEGD 



15 



25 



30 



COF1GURATICN 




BASELIKC CRBITER VEHICLE 


REFERENCE OlhENSIOS 




CENTER OF GRAVITY XO » F5 1076.7 IN. 


WING AREA SVI * 2690.00 


SQ.FT. 


or yo - a. o.o in. 


WING SPAN BW = 78.056 


FT. 


MCt-tNT REFERENCE 20 - UL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


<C£G) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (C€G) 


A 


8 


C 


D 


E 


F 


G 


H 






ELEVON 


PITCHING M 


Ot€NT INCFEJ 


^€NT 






-HO . 000 


0.05250 


0.037MO 


0.029H0 


0.02240 


0.022HO 


0.02420 


0.02860 


. 03650 


-35.000 


0. 04 850 


0.03300 


. 02600 


0.01900 


0.02010 


0.02220 


0.02710 


0.03440 


-30 . 000 


0. OH 350 


0.02750 


0.02150 


0.01550 


0.01750 


0.C2025 


0.02560 


0.03280 


-25.000 


0.03670 


0.02180 


0.01680 


0.01180 


0.01H80 


0.01810 


. 02350 


0.03050 


-20.000 


0.03000 


0.01620 


0.01220 


0.00920 


0.01220 


0.01550 


0.02110 


0.02770 


-15.000 


0.02260 


0.01230 


0.00930 


0.00730 


0.00930 


0.01275 


0.01820 


0.02410 


-10.000 


0.013HO 


0.00740 


0.005H0 


O.OCH40 


0.00640 


0.00930 


0.01410 


0.01870 


-5.000 


0.006HO 


0.00HH0 


. 003HO 


0.002HO 


0.00335 


0.00510 


0.00800 


0. 01060 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00! 10 


-0.00130 


-0.00300 


-Q. 004 20 


-0.00600 


-0.00850 


-0.01200 


-0.01510 


10.000 


-0.00530 


-0.00530 


-0.007H0 


-0.01070 


-0.01530 


-0.02150 


-0.02850 


-0.03600 


15.000 


-0.01060 


-0.01060 


-0.01280 


-0.01880 


-0.02750 


-0.03875 


-0.05050 


-0.06200 


20 . 000 


-0.01780 


-0.01780 


-0 . 02260 


-0.031H0 


-0.04450 


-0.06200 


-0 . 07900 


-0 . 09550 



ENGIhEER B^ 



FIGURE 4.1.1.3-24 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-30 



# 



Rockwell International 

Spac* Division 



MACH NUMBER 



5.000 



DELE CDEGD 

50 -25 

i I i ! | I I I I 



Ul 

o 

Q 




25 30 35 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1076.7 IN. 
OR YO * BL 0.0 IN.. 

MOMENT REFERENCE ZO = WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB =» 1290.3 IN. 



~\ r 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEVCN 


PITCHING M 


Ct-ENT INCRE 


f-ENT 






-^0.000 


0.02420 


0.02860 


0.03650 


0.04650 


0.05S80 


0.07170 


0.08480 


0.09820 


-35.000 


0.02220 


0.02710 


0.03440 


0.04440 


0.05670 


0.06950 


0.08240 


0.09560 


-30.000 


0.02025 


0.02560 


0.03280 


0.04200 


. 05440 


0.06710 


0.07980 


0.09270 


-25.000 


0.01810 


0.02350 


0.03050 


0.03920 


0.05000 


0.06250 


0.07400 


0.08540 


-20.000 


0.01550 


0.02110 


0.02770 


0.03600 


0.04680 


0.05750 


. 06790 


0.07780 


-15.000 


0.01275 


0.01820 


0.02410 


0.03120 


0.03970 


0.04820 


0.05600 


0.06300 


-10.000 


0.00930 


0.01410 


0.01870 


0.02400 


0.03030 


0.03640 


0.04170 


0.04650 


-5.000 


0.00510 


0.00800 


0.01060 


0.01370 


0.01670 


0.01970 


0.02270 


0.02570 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00850 


-0.01200 


-0.01510 


-0.01850 


-0.02250 


-0.02650 


-0.03080 


-0.03540 


10.000 


-0.02150 


-0.02850 


-0.03600 


-0.04370 


-0.05190 


-0.C6010 


-0.06710 


-0 . 07340 


15.000 


-0.03875 


-0.05050 


-0.06200 


-0.07400 


-0.08377 


-0.09270 


-0.09950 


-0.10470 


20.000 


-0.06200 


-0 . 07900 


-0.09550 


-0.11100 


-0.11870 


-0.12390 


-0.12750 


-0.12940 1 



ENGINEER &ZO 
DATE 9/7^/7gZ 



FIGURE 4.1.1.3-25 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-31 



SL72-SH-CCeC 1M 



#J> 



Rockwell International 

Space Division 



MACH 



UJ 

r 
u 
a 



-.1 



■Till 



NUMBER 

Mil 



-.3' ' I I 1 1 1 1 



TTTT 



8.000 

MM 



-50 



DELE 

-25 

-TT-p 



CDEGD 
o 

PTT^- 



25 



It 



I I II 



TT 



TT 




T~rr" r 






"rrr 




-20 



-15 



I I l I II I I M I i I I M ] I M I i I I I M I M I 
-10 -5 5 10 15 ^ 20 

ALPHA CDEGD 



25 



30 









CONHGURATION 










BASELINE ORBITER 


VEHICLE 






REFERENCE 


DlrENSIONS 






CENTER CF GRAVITY 


XO 


» FS 


1076 


7 


IN. 


WING AREA 


sw » 


2690 . 00 


SO.. 


FT. 


OR 


YO 


• BL 








IN. 


WING SPAN 


BW = 


78.056 


FT. 




MOENT REFERENCE 


ZO 


- W. 


375 





IN. 


M.A.C. 


CW - 


39.560 


FT. 
















BCOY LENGTH LS = 


1290.3 


IN. 













ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


to. 000 


15.000 


20.000 


25.000 


DELE (OEG) 


A 


e 


c 


D 


E 


F 


G 


H 






ELEVCN 


PITCHING M 


Ct€NT INCREI 


^£NT 






-M0. 000 


0.05170 


. 03720 


0.02440 


0.01650 


0.01400 


0.01390 


0.02090 


. 02800 


-35.000 


0.04680 


0.03290 


0.02180 


0.01420 


0.01220 


0.01220 


0.01900. 


0.02570 


-30.000 


0.04170 


0.02850 


0.01900 


0.01330 


0.01100 


0.01100 


0.01770 


0.02540 


-25.000 


. 03460 


0.02260 


0.01620 


0.01150 


0.009 10 


0.01010 


0.01620 


0.02270 


-20.000 


0.02750 


0.01710 


0.01260 


0.00990 


. 00790 


0.00990 


0.01440 


0.02170 


-15.000 


0.02090 


0.01380 


0.01100 


0.00880 


0.00700 


0.00900 


0.01230 


0.01900 


-10.000 


0.01190 


0.00760 


0.00690 


0.00620 


0.00430 


0.00620 


0.00950 


0.01510 


-5.000 


0.00730 


0.00490 


0.00450 


0.00410 


0.00320 


. 00420 


0.00580 


. 00930 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00080 


-0.00080 


-0.00200 


-0 . 00350 


-0.00640 


-0 . 00800 


-0.01150 


-0.01470 


10.000 


-0.00250 


-0.00260 


-0.00510 


-0.00800 


-0.01380 


-0.02040 


-0.02750 


-0.03500 


15.000 


-0.00320 


-0.00310 


-0.00650 


-0.01180 


-0.02210 


-0 . 03360 


-0.04950 


-0 . 06250 


20.000 


-0.01420 


-0.01400 


-0.01840 


-0.02800 


-0.04230 


-0.06100 


-0.08200 


-0 . 09900 



ENGINEER S*^ 

oaiz_j?J7S£z£ 



ELEVCN 



FIGURE 
PITCHING 



4.1.1.3 
MOMENT 



-26 

COEFFICIENT 



INCREMENT 



4.1.1.3-32 




Rockwell International 

Space Division 



NUMBER 
TT1 



DELE CDEG3 

-25 25 



LU 

z: 
o 
a 




25 30 35 

ALPHA CDEG] 



CONFIGURATION 


BASELINE 0R9ITER VEHICLE 


REFERENCE OIKtNSIONS 


CENTER Of GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW • 78.055 FT. 


MCtOJT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.1 IN. 



C€LE <C€G) 



-40.000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20 . 000 



ALPHA (DEG) 



15.000 
F 



20.000 
G 



25.000 
H 



30 . 000 
I 



35.000 
J 



HO. 000 
K 



45.000 

L 



50 . 000 
M 



ELEVCN PITCHING MCftNT INCREfENT 



0.01390 

0.01220 

0.01100 

0.01010 

. 00990 

0.00900 

. 00520 

. 00420 

0.0 

-0 . 00800 

-0.02040 

-0.03360 

-0.05100 



. 02090 

0.01900 

0.01770 

0.01620 

0.01440 

0.01230 

0.00950 

. 00580 

0.0 

-0.01150 

-0.02750 

-0 . 04950 

-0.08200 



0.02800 
. 02670 
0.02540 
. 02270 
0.02170 
0.01900 
0.01510 
. 00930 
.0 

.01470 
.03500 
.06250 
.09900 



! ENGINEER &C& 



0.03850 
0.03700 
0.03510 
. 03300 
0.03040 
0.02630 
0.02160 
0.01275 
0.0 
-0.01745 
-0.04250 
.07500 
11300 



-0. 
-0. 



0.05070 
. 04900 
0.04675 
. 04400 
0.04050 
0.03435 
0.02700 
0.01560 
0.0 

-0.02150 
-0.05040 
-0.08500 
-0.12550 



. 06520 

0.06260 

0.05950 

0.05570 

. 05040 

. 04250 

0.03200 

0.01800 

0.0 

-0.02370 

-0 . 05550 

-0.09750 

-0.14000 



0.07320 
0.07550 
0.07250 
0.06780 
0.06130 
0.05200 
0.03940 
0.02210 
0.0 

-0.02750 
-0.06100 
-0.10950 
-0.16750 



0.09020 

0.08750 

0.08340 

0.07730 

0.06900 

0.05780 

. 04330 

0.02400 

0.0 

-0.03150 

-0 . 07000 

-0.12100 

-0.18850 



FIGURE 4.1.1.3-27 
ELEVGN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-33 



SD72-SK-CCC C 



ivi 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



DELE 
-50 -25 

M i i i | 



CDEG) 
o 

!Mf 



.1 



Ul 

8 



r i i i i i i i i 



-.3L1 

-20 



TTTT 




TTT 



i [ I 



n~r 



1 



rrr" 



1 1 



FS^ 



1 1 1 1 1 1 1 1. 1 1 






1 1 i 1 



1 1 1 1 l 1 



1 1 1 



■i 1 1 1 I 1 1 1 




•15 



-10 



5 10 

ALPHA CDEGD 



15 



20 



25 



CONFIGURATION 




BASELINE CRB1TER VEHICLE 


REFERENCE PENSIONS 




CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 


FT. 


M0r£NT REFERENCE ZO - ML 375.0 IN. 


M.A.C. CW « 39.560 


FT. 




8COY LENGTH LB - 1290.3 


IN. 



£M3JNEER SC& 



ELEVGN 



FIGURE 4.1.1.3-28 

PITCHING MOMENT COEFFICIENT INCREMENT 



30 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






ELEVON 


PITCHING M 


GtENT INCRE 


~ENT 






-HO. 000 


0.05170 


0.03720 


. 02440 


0.01650 


0.01400 


0.01390 


. 02090 


. 02900 


-35.000 


0.04680 


0.03290 


0.02180 


0.01420 


0.01220 


0.01220 


0.01900 


. 02570 


-30.000 


0.04170 


0.02850 


0.01900 


0.01330 


0..01100 


0.01100 


0.01770 


. 02540 


-25.000 


0.03460 


0.02250 


0.01620 


0.01150 


0.00910 


0.01010 


0.01520 


. 02270 


-20.000 


0.02750 


0.01710 


0.01260 


0.009SO 


0.00790 


0.00S90 


0.01440 


0.02170 


-15.000 


0.02090 


0. 01380 


0.01100 


0.00880 


0.00700 


0.00900 


0.01230 


0.01900 


-10.000 


0.01190 


0.00750 


0.00690 


0.00620 


0.00430 


0.00620 


0.00950 


0.01510 


-5.000 


0.0073O 


0.00490 


0.00450 


0.00410 


0.00320 


0.00420 


0.00580 


0.00930 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00080 


-0.00080 


-0.00200 


-0.00350 


-0.00640 


-0.00800 


-0.01150 


-0.01470 


10.000 


-0 . 0O25O 


-0.00250 


-0.00510 


-0.00800 


-0.01380 


-0.02040 


-0.02750 


-0 . 03500 


15.000 


-0.00320 


-0.00310 


-0.00650 


-0.01180 


-0.02210 


-0.03360 


-0 . 04950 


-0.06250 


20.000 


-0.0 1420 


-0.01400 


-0.01840 


-0.02800 


-0 . 04230 


-0.06100 


-0.08200 


-0.09900 



4.1.1.3-34 



0im Rockwell International 

Space Division 



L 



MACH NUMBER 



10.000 



OELE CDEG) 

-50-25 

| I I I 1 | l I : I 



LU 

o 
o 




ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER ^ICLE 


REFERENCE DIl-ENSlONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - 8L 0.0 IN. 


WING SPAN BW = 78.056 FT. 


MOMENT REFERENCE 20 • WL 375.0 IN. 


M.A.C. CW =■ 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 



C€L£ (DEG) 



-H0.0O0 
-35.000 
-30.000 
-25.000 

-eo.ooo 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (DEG) 



15.000 

F 



20.000 
G 



25.000 
H 



30 . 000 
I 



35.000 
J 



40.000 
K 



H5.000 
L 



ELEVON PITCHING MCf-CNT INCREMENT 



0.01390 
0.01220 
0.01100 
0.01010 
0.00990 
. 00900 
0.00620 
0.00420 
0.0 

-0.00800 
-0 . 02040 
-0.03360 
-0.06100 



0.020S0 
0.01900 
0.01770 
0.01620 
0.01440 
.01230 
.00950 
.00580 
.0 

-0.01150 
-0.02750 
-0.04950 
-0.08200 



0.02800 

0.02670 

0.02540 

0.02270 

0.02170 

0.01900 

0.01510 

. 00930 

0.0 

-0.01470 

-0.03500 

-0.06250 

-0 . 09900 



ENGINEER &<& 
-DATE____377 



0.03850 

0.03700 

0.03510 

0.03300 

0.03040 

0.02580 

0.02160 

0.01275 

0.0 

-0.01745 

-0 . 04250 

-0 . 07500 

-0.11300 



0.05070 

0.04900 

0.04675 

0.04400 

0.04050 

0.03485 

0.02700 

0.01550 

0.0 

-0.02150 

-0.05040 

-0.08500 

-0.12550 



0.06520 

0.06260 

0.05950 

0.05570 

0.05040 

0.04250 

0.03200 

0.01800 

0.0 

-0.02370 

-0.05550 

-0.09750 

-0.14000 



0.07820 
0.07550 
0.07250 
. 06780 
06130 
0.05300 
0.03940 
02210 


02750 
06100 
10950 
16750 



FIGURE 4.1.1.3-29 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



50.000 
M 



0.09020 

0.08750 

0.08340 

0.07730 

. 06900 

0.. 05780 

0.04330 

0.02400 

0.0 

-0.03150 

-0.07000 

-0.12100 

-0.18850 



4.1.1.3-35 



SE72-SH-0CCC 1 M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 



15.000 



DELE CDEGD 

- 50 -25 25 

| I I i I | l I i l | I I I I 



Ul 

U 
Q 




-.2 



-20 



-10 



5 10 

ALPHA CDEGD 



30 



CONFIGURATION 




BASELINE CR8ITER VEHICLE 


REFERENCE OirCNSIONS 




CENTER OF GRAVITY X0 - FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YD - BL 0.0 IN. 


WINS SPAN BW » 78.056 


FT. 


MCfENT REFERENCE 20 - UL 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




900Y LENGTH LB - 1290.3 


IN. 



OELE (DEG1 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0,0 

5.000 

10.000 

15.000 

20.000 



ALPHA (CEG) 



-10.000 
A 



-5.000 
8 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



20.000 
G 



ELEVCN PITCHING MOMENT INCREfENT 



0.05170 
0.04680 
0.04170 
0.03460 
0.02750 
0.02090 
0.01190 

.00730 

.0 

.00080 

.00250 
-0.00320 
-0.01420 



0. 

0. 
-0. 
-0. 



0.03720 

0.03290 

0.02850 

0.02260 

0.01710 

0.01380 

0.00760 

0.00490 

0.0 

-0.00080 

-0.00260 

-0.00310 

-0.01400 



0.02440 
0.02180 
0.01900 
0.01620 
.01260 
.01100 
.00690 
.00450 
.0 

-0.00200 
-0.00510 
-0.00650 
-0.01840 



0.01650 

0.01420 

0.01330 

0.01150 

0.00990 

0.00880 

0.00620 

0.00410 

0.0 

-0-00350 

-0.00800 

-0.01180 

-0.02800 



0.01400 

0.01220 

0.01100 

0.00910 

0.00790 

0.00700 

0.00430 

0.00320 

0.0 

-0.00640 

-0.01380 

-0.02210 

-0.04230 



0.01390 

0.01220 

0.01 100 

0.01010 

0.00990 

0.00900 

0.00620 

0.00420 

0.0 

-0.00800 

-0.02040 

-0.03360 

-0.06100 



. 02090 
0.01900 
0.01770 
0.01620 
0.01440 
0.01230 
0.00950 
0.00580 
0.0 

-0.01150 
-0 . 02750 
-0.04950 
-0 . 0B200 



ENGINEER Q&> FIGURE 4.1.1.3 

date ZzfcTlJ ELEVON PITCHING MOMENT 



•30 

COEFFICIENT INCREMENT 



25.000 
H 



0.02800 
0.02670 
0.02540 
0.02270 
0.02170 
0.01900 
0.01510 
. 00930 
0.0 

-0.01470 
-0.03500 
-0.06250 
-0 . 09900 



U. 1.1. 3-36 



SD72 -s;;- c:ec im 



Igl 



Rockwell International 

Space Division 



MACH NUMBER 



15.000 



LlI 

T. 
U 

a 



-.1 



I I I I I I IT I I ! I I I I I ! ! I 



DELE CDEGJ 

-50 -25 

I I I i | I I I 



25 



i i I i i i rrrrr 



■ 3 Li...L- l 1..1 i i i i I i i i i I i i i i I i 

5 10 15 20 25 



JSi53S?Pl£E 




ttt\ — rrr 



L-L-Li-L I I I I I I I I I ! I I 



T-TTT 



< : i 



30 35 

ALPHA CDEGD 



40 



45 



1_L.J_1_L.1_ 
50 55 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIh€NSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SU » 2690.00 


SO. FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W » 78.056 


FT. 


MCf_NT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 











ALPHA 


(CEG) 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (CEG) 


F 


G 


H 


I 


J 


K 


L 


M 






ELEVON 


PITCHING M 


OMENT INCRE 


f-ENT 






-HO. 000 


0.01390 


0.02090 


0.02800 


0.03850 


0.05070 


0.06520 


0.07820 


0.09020 


-35.000 


0.01220 


0.01900 


. 02670 


0.03700 


0.04900 


0.06260 


0.07550 


0.08750 


-30.000 


0.01100 


0.01770 


0.02540 


0.03510 


0.04675 


0.05950 


0.07250 


0.08340 


-25.000 


0.01010 


0.01620 


0.02270 


0.03300 


0.04400 


0.05570 


0.06780 


0.07730 


-20.000 


0.00990 


0.01440 


0.02170 


0.03040 


0.04050 


0.05040 


0.06130 


0.06900 


-15.000 


0.00900 


0.01230 


0.01900 


0.02680 


0.03485 


0.04250 


0.05200 


0.05780 


-10.000 


0.00620 


0.00950 


0.01510 


0.02160 


0.02700 


0.03200 


. 03940 


0.04330 


-5.000 


0.00420 


0.00580 


0.00930 


0.01275 


0.01560 


0.01800 


0.02210 


0.02400 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00800 


-0.01150 


-0.01470 


-0.01745 


-0.02150 


-0.02370 


-0 . 02750 


-0.0315O 


10.000 


-0.02040 


-0.02750 


-0.03500 


-0.04250 


-0.05040 


-0.05550 


-0.06100 


-0 . 07000 


15.000 


-0.03360 


-0.04950 


-0 . 05250 


-0.07500 


-0.08500 


-0.09750 


-0.10950 


-0.12100 


20.000 


-0.06100 


-0.08200 


-0.09900 


-0. 11300 


-0.12550 


-0.14000 


-0.16750 


-0.13850 



ENGINEER QCO 
OATE JZUFlll 



FIGURE 4.1.1.3-31 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-37 



SL 7? -£!-:• CCCC 1M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 

■ 3 M I I I I I i i 



20.000 



DELE CDEGD 

- 50 -25 25 

| I I I I | I I I I | I I I I 



UJ 

u 




-20 



5 10 

ALPHA CDEGD 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DlfENSICNS 




CENTER OF GRAVITY XO ' FS 1075.7 IN. 


WING AREA SU - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WINS SPAN BW - 78.056 


FT. 


MCfCNT REFERENCE ZO = M. 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 



CELE (OEG) 



-MO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (OEG) 



-10.000 
A 



-5.000 
8 



0.0 
C 



5.000 




10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H 



ELEVON PITCHING MOMENT INCRETCNT 



0.05170 
0.04680 
0.04170 
0.03460 
0.02750 
0.02090 
0.01190 
0.00730 
0.0 
.00080 
.00250 
.00320 
.01420 



0.03720 

0.03290 

0.02850 

0.02260 

0.01710 

0.013S0 

0.00760 

0.00490 

0.0 

-0.00080 

-0 . 00260 

-0.00310 

-0.01400 



0.02440 

0.02180 

0.01900 

0.01520 

0.01260 

0.01100 

0.00690 

0.00450 

0.0 

-0.00200 

-0.00510 

-0.00650 

-0.01840 



ENGINEER &££ 
OATE ".Rjl^JOJ 



0.01650 

0.01420 

0.01330 

0.01150 

0.00990 

0.00880 

0.00620 

0.00410 

0.0 

-0.00350 

-0.00800 

-O.OU80 

-0.02800 



0.01400 

0.01220 

0.01100 

0.00910 

0.00790 

. 00700 

0.00430 

0.00320 

0.0 

-0.00640 

-0.01380 

-0.02210 

-0.04230 



0.01390 

0.01220 

0.01100 

0.01010 

0.00990 

0.00900 

0.00620 

0.00420 

0.0 

-0.00800 

-0.02040 

-0.03360 

-0.06100 



0.02090 
0.0190Q 
0.01770 
0.01620 
0.0 1440 
0.01230 
0.00950 
0.00580 
0.0 

-0.01150 
-0.02750 
-0.04950 
-0.08200 



0.02800 
0.02670 
0.02540 
0.02270 
0.02170 
0.019C0 
0.01510 
0.00930 
0.0 

-0.01470 
-0.03500 
-0.06250 
-0.09900 



FIGURE 4.1.1.3-32 
ELEVQN PITCHING MOMENT COEFFICIENT INCREMENT 



4.1.1.3-38 



CCLC 1M 




Rockwell International 

Spaca&visJon 



JL 



NUMBER 



20.000 

i"i "i r 



DELE 
-as 



lu 

2: 
u 

Q 




25 30 35 

ALPHA CDEG) 



CONFIGURATION 




BASELINE OR8ITER VEHICLE 


REFERENCE Olt-OSIONS 




CENTER OF GRAVITY XO - FS 107S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO « BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. •' 


MCf-ENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 



OELE (PEG) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



15.000 

F 



20 . 000 
G 



ALPHA (OEG> 



25.000 
H 



30.000 
I 



35.000 
J 



40.000 
K 



45.000 
L 



50.000 
M 



0.01390 
0.01220 
0.01100 
0.01010 
0.00990 
0.00900 
0.00620 
00420 


00800 
02040 
03360 



-0.06100 



0.02090 
0.01900 
0.01770 
0.01620 
0.01440 
.01230 
.00950 
.00580 
.0 

-0.01150 
-0.02750 
-0 . 04950 
-0 . 08200 



ELEVCN PITCHING M>£NT INCREMENT 



0.02800 

0.02670 

0.02540 

0.02270 

0.02170 

0.01900 

0.01510 

0.00930 

0.0 

-0.01470 

-0.03500 

-0.06250 

-0.09900 



ENGINEER 
OATE_ 



0.03850 

0.03700 

0.03510 

0.03300 

0.03040 

0.02680 

0.02160 

0.01275 

0.0 

-0.01745 

-0.04250 

-0.07500 

-0.11300 



0.05070 
0.04900 
0.04675 
0.04400 
0.04050 
0.03485 
0.02700 
0.01550 
0.0 

-0.02150 
-0.05040 
-0.08500 
-0.12550 



0.06520 
0.06260 
0.05950 
0.05570 
0.05040 
0.04250 
0.03200 
0.01800 
0.0 

-0.02370 
-0.05550 
-0.09750 
-0.14000 



0.07820 
0.07550 
0.07250 
0.06780 
0.06130 
0.05200 
0.03940 
0.02210 
0.0 

-0.02750 
-0.06100 
-0.10950 
-0.16750 



0.09020 

0.08750 

0.08340 

0.07730 

0.06900 

0.05780 

0.04330 

. 02400 

0.0 

-0.03150 

-0 . 07000 

-0.12100 

-0.1S850 



JSE8 



FIGURE 4.1.1.3-33 
ELEVON PITCHING MOMENT COEFFICIENT INCREMENT 



4.1-1.3-39 



£L 71-3H-CC6C JM 



'i* 



Rockwell International 

Space Division 



VBAR 



0.005 



DELE CDEG) 

50 -25 

! I l I > | I I I I 



25 




30 35 

ALPHA CDEG 3 



50 



55 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO » 8L 0.0 IN. 


WING SPAN BW = 79.056 FT. 


MOMENT REFERENCE ZO - 14. 375.0 IN. 


M.A.C. CW = 39.550 FT. 




BCOY LENGTH LB =■ 1290.3 IN. 



ENGINEER 
DATE I 





ALPHA (OEG) 


20.000 


25.000 


30 . 000 


35.000 


40 .000 


45.000 


50.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 






ELEVON PITC 


HING MOMENT 


COEFFICIE 






-40.000 


0.02090 


. 02800 


0.03850 


0.05070 


0.06520 


0.07820 


. 09020 


-35.000 


0.01900 


0.02670 


. 03700 


. 04900 


0.06260 


0.07550 


. 08750 


-30.000 


0.01770 


0.02540 


0.03510 


. 04675 


0.05950 


0.07250 


. 08340 


-25.000 


0.01S20 


. 02270 


. 03300 


0.04400 


. 05570 


0.06780 


. 07730 


-20.000 


0.01440 


0.02170 


. 03040 


0.04050 


. 05040 


0.06130 


. 06900 


-15.000 


0.01230 


0.01900 


0.02680 


0.03485 


. 04250 


0.05200 


. 05780 


-10.000 


0.00950 


0.01510 


0.02160 


0.02700 


0.03200 


0.03940 


0.04330 


-5.000 


. 00580 


. 00930 


0.01275 


0.01560 


0.01800 


0.02210 


0.02400 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01150 


-0.01470 


-0.01745 


-0.02150 


-0 . 02370 


-0.02750 


-0.03150 


10.000 


-0.02750 


-0.03500 


-0 . 04250 


-0.05040 


-0.05550 


-0.06100 


-0.07000 


15.000 


-0.04950 


-0 . 06250 


-0.07500 


-0.08500 


-0.09750 


-0.10950 


-0.12100 


20.000 


-0.08200 


-0 . 09900 


-0.11300 


-0.12550 


-0.14000 


-0.15750 


-0.'.8850 


SA 


FIG 


SURE 4. 


t . 1 . 3-34 











EFFECT 



4.1.1.3-40 



C r - ry 



-?;-.-cceo im 



#1% 



Rockwell International 
Space Division 



VBAR 



.10 



.05 



LLl 



-.05 



-.10 



,15 



-.30 



ti n n r 



COEG) 

25 

I l I | I I I i 



10 




30 35 

ALPHA CDEG] 



CONFIGURATION 




BASELINE 0R81TER VEHICLE 


REFERENCE 1 MENS IONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW » 2590.00 


SQ.FT. 


OR yo - a. 0.0 IN. 


WING SPAN 3W » 78.056 


FT. 


MOMENT REFERENCE ZO • WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BOOY LENGTH LB « 1290 . 3 


IN. 



ENGINEER 
DATE " 



NASA 



FIGURE 



4.1.1 

EFFECT 



.3-35 
OF ELEVON 









ALPHA (OEG) 








20.000 


25.000 


30 . 000 


35.000 


40 . 000 


45.000 


50 . 000 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 






ELEVON PITC 


HING MOMENT 


COEFFICIE 






-HO. 000 


0.01920 


0.02720 


. 03770 


0.04980 


. 06470 


. 07790 


0.08980 


-35.000 


0.01920 


. 02630 


0.03690 


0.04930 


0.06350 


0.07710 


0.08720 


-30.000 


0.01800 


0.02560 


. 03480 


0.04580 


. 05970 


0.07370 


0.08190 


-25.000 


0.01560 


. 02360 


0.03300 


0.04400 


0.05570 


0.06940 


0.07600 


-20.000 


0.01390 


0.02070 


0.02950 


0.03870 


0.05040 


0.06100 


0.06850 


-15.000 


0.01160 


0.01720 


0.02570 


0.03300 


0.04250 


0.05180 


0.05730 


-10.000 


0.00790 


0.01310 


0.01910 


. 02400 


0.03200 


0.03820 


. 04330 


-5.000 


0.00600 


0.00630 


. 00970 


0.01460 


0.01800 


0.02170 


. 02400 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01150 


-0.0 1470 


-0.01750 


-0.02200 


-0.02370 


-0 . 02720 


-0.02950 


10.000 


-0.02700 


-0.03540 


-0. OH 350 


-0.05040 


-0 . 05550 


-0.06000 


-0.06300 


15.000 


-0.04810 


-0.06210 


-0.07850 


-0 . 08580 


-0.09800 


-0.10250 


-0.12040 


20.000 


-0 . 08200 


-0.09900 


-0.11300 


-0.12550 


-0.14000 


-0.16750 


-0.18850 



4.1.1.3-41 



sc 7::-3K-ccec im 



'Jt 



Rockwell International 

Space Division 



u 
o 




-.10 



25 30 35 

ALPHA CDEG] 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SU =• 2690.00 SO. FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MCftNT REFERENCE ZO > WL 375.0 IN. 


M.A.C. CW ■ 39.560 FT. 




BCCY LENGTH LB = 1290.3 IN. 



ENGINEER NAgA 
DATE ™ 





ALPHA (DEG) 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50 . 000 


DELE (DEG) 


A 


B 


C 





E 


F 


G 






ELEV0N PITC 


HING MOTENT 


COEFF1CIE 






-HO. 000 


0.01920 


. 02720 


0.03770 


0.04980 


0.06470 


. 07790 


0.08980 


-35.000 


0.01920 


0.02630 


0.03690 


0.04930 


0.06350 


0.07710 


0.08720 


-30.000 


0.01800 


0.02560 


0.03480 


0.04580 


0.05970 


0.07370 


0.08190 


-25.000 


0.01560 


. 02360 


. 03300 


0.04400 


0.05570 


0.06940 


0.07600 


-20.000 


0.01330 


0.02070 


0.02950 


. 03870 


. 05040 


0.06100 


. 06850 


-15.000 


0.01160 


0.01720 


0.02570 


0.03300 


0.04250 


0.05180 


0.05730 


-10.000 


0.00790 


0.01310 


0.01910 


0.02400 


0.03200 


0.03820 


0.04330 


-5.000 


0.00600 


. 00630 


0.00970 


0.01460 


0.01800 


0.02170 


0.02400 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01 150 


-0. 01*70 


-0.01750 


-0.02200 


-0 . 02370 


-0.02720 


-0.02950 


10.000 


-0.02700 


-0.03540 


-0.04350 


-0.05040 


-0 . 05550 


-0.06000 


-0.06300 


15.000 


-0.04810 


-0.06210 


-0 . 07850 


-0.08180 


-0 . 08700 


-0 . C9020 


-0.09840 


20 . 000 


-0 . 08200 


-0 . 09900 


-0.11300 


-0.11970 


-0.12200 


-0.13200 


-0 . 1 3500 




FIC 


iURE 4. 


1.1.3-36 











EFFECT OF ELEVGN 



4.1.1.3-42 



*^J 



L 



CCA. C 1M 



m 



Rockwell International 

Space Omscv! 



ALTITUDE CFT. ) = 300000.0 to 600,OCO.O 
■ l0 ' I I I I 



DELE (DEC ) 

-50 -25 25 

I | I I I I j i I I i 



.05 



H 



.05 



.10 



.15 



I I i I I i I I i TT~T 



10 




30 35 

ALPHA CDEGD 



COflGURATION 


BASELIf^ ORSITER VEHICLE 


REFERENCE DI^NSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WINS AREA SW » 2690.00 SQ.FT. 


OR YO - a. 0.0 IN. 


WING SPAN BW » 78.055 FT. 


MOtCNT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BCOY LENGTH LB » 1290.3 IN. 



ENGINEER 
DATE " 









ALPHA (DEG) 








20.0 


25.0 


30.0 


35.0 


40.0 


45.0 


50.0 


DELE (OEG) 


A 


B 


C 


D 


E 


F 


G 






ELEVON PITC 


HING MOENT 


CGEFFICIE 






-40.000 


0.01920 


0.02720 


. 03770 


0.04980 


0.06470 


0.07790 


0.08980 


-35.000 


0.01920 


0.02630 


0.03690 


0.04930 


0.06350 


0.07710 


0.08720 


-30.000 


0.01800 


0.02560 


0.03480 


0.04580 


0.05970 


. 07370 


0.08190 


-25.000 


0.01560 


0.02360 


0.03300 


0.04400 


0.05570 


0.06940 


. 07600 


-20.000 


0.01390 


0.02070 


0.02950 


0.03870 


0.05040 


0.06100 


0.06850 


-15.000 


0.01160 


0.01720 


0.02570 


0.03300 


0.04250 


0.05180 


0.05730 


-10.000 


0.00790 


0.01310 


0.01910 


0.02400 


0.03200 


0.03820 


0.04330 


-5.000 


0.00600 


0.00630 


. 00970 


0.01460 


0.01800 


0.02170 


0.02400 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01150 


-0.01470 


-0.01750 


-0.02200 


-0.02370 


-0.02720 


-0.02950 


10.000 


-0 . 02700 


-0.03540 


-0 . 04350 


-0.05040 


-0. 05550 


-0.06000 


-0.06300 


15.000 


-0.04810 


-0.06210 


-0.07850 


-0.08180 


-0.08700 


-0.09020 


-0 . 09840 


20.000 


-0 . C8200 


-0 . 09900 


-0.11300 


-0.11970 


-0.12200 


-0 . 1 3200 


-0 . 1 3500 


ISA 


FIG 


>URE 4. 


.1.3-37 











EFFECT OF ELEVON 



4.1.1.3-43 



f r *? <" 



-GH-CC6C 1M 



#1% 



Rockwell international 

Spac* Division 

__x 



T. 



1.0 



0.8 



0.5 



0.4 



0.2 




rr v 



i i i i 



i i t r 



i i i r 






~=l^a- v:w\t\\: >. WW 






V.,?- 5 ' 



rS \ tfl ^ft v|jl , j: .-^...-^...vvr-za 




0.5 1.0 15 2.0 2.5 

MACH NUMBER 



3.0 



3.5 



4.0 



CONFIGURATION 




BASELINE ORBITER VEHICLE REFERENCE OlrOSICffi 




CENTER OF GRAVJTY X0 • FS 1076.7 IN. WINS AREA SW - 2690.00 


so.rr. 


OR YO • 8L 0.0 IN. WINS SPAN BW » 78.056 


FT. 


MCfrCNT REFERENCE ZO - U. 375.0 IN. M.A.C. CW - 39.560 


FT. 


WTY LENGTH LB - 1250.3 


IN. 





C€l e (DEG) 




-5.000 


0.0 


5.000 


MACH MJfBER 


A 


9 


C 


PITCHING MC 


m. partial 


span factor 


0.250 


0.60000 


0.60000 


0.60000 


0.400 


0.60000 


0.50000 


0.60000 


0.600 


0.60000 


0.60000 


0.60000 


0.800 


0.68000 


0.65000 


0.58000 


0.900 


0.60000 


0.73000 


0.57000 


0.950 


O.S3000 


0.76000 


0.58000 


0.9BO 


0.94000 


0.77000 


0.59000 


1.050 


0.84000 


0.77000 


0.63000 


1.100 


0.93000 


0.77000 


0.55000 


1.200 


0.80000 


0.75000 


0.67000 


1.300 


0.77000 


0.73000 


0.57000 


1.500 


0.72000 


0.69000 


0.67000 


2.000 


0.67000 


0.67000 


0.67000 


3.000 


0.67000 


0.67000 


0.67000 


4.000 


0.67000 


O.S7000 


0.57000 


5.000 


0.67000 


O.S7000 


0.87000 


8.000 


0.67000 


0.67000 


0.57000 


10.000 


0.57000 


0.67000 


. 57000 


15.000 


0.67000 


0.67000 


0.67000 


a. ooo 


0.S7000 


1 0.S7OOO 


0.67000 



NOTE: In cne event part 111 
ipan factor? are 
required «nicn exceed 
;ne ?! ven I imi ts, the 
Aero Data Jni t at 
Rockwell tnternatton' ! 
should be contacted 
iefcri extrapolation 
of Che given daca. 



ENGINEER 

0ATE9 






FIGURE 4.1.1.3-38 

FtFVflN PARTIAL SPAN FACTOR 



4.1.1.3-W* 



CCCC IM 



wjj^ 



Rockwell International 

Space Divis**-) 



MACH NUMBER 



0.250 



0EL8F CDEGj 

55 25 

i r r 



u 

Q 



-.08 




CONFIGURATION 



BASEL I h£ ORB ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO • EC 0.0 IN. 

MOMENT REFERENCE ZO =• WL 375.0 IN. 



REFERENCE 
WING AREA 
WING SPAN 
M.A.C. 



DIMENSIONS 
SW » 2690.00 SQ.FT. 
8W » 78.056 FT. 
CW = 39.560 FT. 



BCOY LENGTH L9 » 1290.3 IN. 











ALPHA 


(DEG) 









-10.000 


-5.000 


0.0 


5.000 


1 . 000 


15.000 


20.000 


25.000 


OELBF .(DEG) 


A 


B 


c 





E 


F 


G 


H 






BCOY F 


LAP PITCHIN 


G MOMENT CO 


EFF1 






-11.700 


0.01470 


0.01530 


0.01580 


0.01700 


0.01900 


0.01810 


0.01900 


0.01900 


-5.000 


0.00670 


0.00690 


0.00710 


. 00820 


0.00800 


. 00820 


0.00850 


0.00850 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00990 


-0.00940 


-0.00900 


-0.00924 


-0.00880 


-0 . 00970 


-0.00900 


-0.00900 


10.000 


-0.02000 


-0.01930 


-0.01860 


-0.01860 


-0.01800 


-0.01900 


-0.01820 


-0.01820 


16.300 


-0.03110 


-0.03100 


-0.03100 


-0 . 03050 


-0.03070 


-0.03090 


-0.03040 


-0.03040 


22.500 


-0 . 03830 


-0 . 04050 


-0 . 04240 


-0.04500 


-0.04530 


-0 . 04500 


-0.04200 


-0.04200 



EhC [f £ER_r^b 



FIGURE 4.1.1.3-39 
EFFECT OF BODV FLAP 



4.1.1.3-45 



c r - 



C 72-SH-GCeC 1M 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 

■ 04 n i i i i i i i i 



0.400 



DELBF CDEG) 

-25 25 

III! 



CD 

r 
u 
a 




-.08 



-15 



5 10 

ALPHA CDEGD 



CCfFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO • WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW ■ 39.560 FT. 

BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 000 


25.000 


CCL3F <DEG) 


A 


8 


C 





E 


F 


G 


H 






BCOY FLAP PITCHING MOMENT COEFFI 






- 1 1 . 700 


0.01490 


0.01550 


0.01600 


0.01720 


0.01900 


0.01900 


0.02000 


0-02000 


-5.000 


0.00710 


0.00730 


0.00750 


0.00750 


0.00867 


0.00860 


. 00890 


. 008SO 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0 . 00970 


-0.00930 


-0.00690 


-0.00924 


-0 . 00925 


-0.00947 


-0.00910 


-0.00910 


10.000 


-0.01950 


-0.01680 


-0.01810 


-0.01880 


-0.01890 


-0.01910 


-0.01870 


-0.01870 


16.300 


-0.03100 


-0.03110 


-0.03110 


-0.03130 


-0.03170 


-0.03190 


-0.03100 


-0.03100 


22.500 


-a . oho i o 


-0.04230 


-0 . 04420 


-0 . 04660 


-0.0^600 


-0.04610 


-0.04310 


-0.04310 



ENGINEER £&£> 
DATE l§r3-35 



FIGURE 4.1.1.3-40 

EFFECT OF BODY FLAP 



4.1.1.3-46 



r • r- 



i-.-OcLC 1M 



*i* 



Rockwell International 

Space Division 



MACH NUMBER 



DELBF CDEG) 

25 25 

I I i I I i I I 



u. 

CD 

u 
a 




CONFIGURATION 




BASELINE ORBITED VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO => FS 1076.7 IN. 


WING AREA SU = 2690.00 


SQ.FT 


OR YO - 9L 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MOMENT REFERENCE ZO • \4- 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BOOY LENGTH L8 =» 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (OEG) 


A 


8 


C 





E 


F 


G 


H 






BOOY 


FLAP PITCH! 


NG MOMENT I 


NCR. 






-11.700 


0.01800 


0.01814 


0.01790 


0.01896 


0.02012 


0.02135 


. 02300 


. 02H0O 


-5.000 


. 00835 


0.00840 


0.00831 


0.00872 


0.00906 


0.00952 


0.00997 


0.01030 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00942 


-0.00946 


-0 . 00942 


-0 . 00969 


-0.00978 


-0.01014 


-0.01012 


-0.01033 


10.000 


-0.01983 


-0.01988 


-0.01983 


-0 . 02030 


-0.02024 


-0.02C87 


-0 . 02038 


-0.02067 


16.300 


-0.03400 


-0.03406 


-0 . 03394 


-0.03487 


-0.03428 


-0.03512 


-0 . 03400 


-0.03400 


22.500 


-0 . 04900 


-0.04905 


-0 . 04880 


-0 . 05C45 


-0.04897 


-0 . 04990 


-0.04900 


-0 . 05000 



ENGINEER w»*_ 

J DATE Za£S£C8 



FIGURE 4. 1.1.3-a 

EFFECT OF BOOY FLAP 



4.1.1.3-^7 



c r "T <r o 



CCCC 1M 



'1* 



Rockwell International 

Space Division 






MACH NUMBER 



0.800 



DELBF CDEG) 

-25 25 



-OH 



.02 



u. 
CD 

u 

Q 



-.02 



-.04 



-.06 



-.08 



-.10 




1 L 1.1. 



I I 



I ! I I 



I I I I 



1 I 1 I 



_L_L- 



III! 



-15 



-10 



-5 



5 

ALPHA 



to 
CDEG) 



15 



20 



25 



30 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER Cf GRAVITY XO - FS 1076.7 IN. 


WING AREA SW = 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW * 78.056 


FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB =■ 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BOOY 


FLAP PITCHI 


NG MOMENT I 


VCR. 






-11.700 


. 02000 


0.C2017 


. 02040 


0.02163 


0.02182 


0.02303 


0.02400 


. 02500 


-5.000 


0.00944 


0.00948 


0.00964 


0.01004 


0.01017 


0.01078 


o.oi ne 


0.01165 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01157 


-0.01136 


-0.01226 


-0.01149 


-0.01183 


-0.01264 


-0.01277 


-0.01313 


10.000 


-0.02403 


-0 . 02376 


-0.02523 


-0.02412 


-0.02493 


-0 . 02655 


-0.02691 


-0.02771 


16.300 


-0.04000 


-0.03986 


-0.04092 


-0.04092 


-0.04196 


-0.04482 


-0.04600 


-0.04800 


22.500 


-0.05600 


-0.05615 


-0.05562 


-0.05823 


-0.05951 


-0.06350 


-0.06600 


-0.07000 



Oate II€rX«L- 7 6 



FIGURE 4.1.1.3-^2 

, EFFECT OF BODY FLAP 



k. 1.1. 3-48 



* 



Rockwell International 

Space Division 



MACH NUMBER 



0.900 



DELBF CDEGD 

-25 25 

I i i i i I I i~i — ; — ! 



.OH 



.02 



lo- 
rn 

T. 
CJ 
Q 



-.02 



-.04 



.06 



-.08 



.10 



TT'I I I I I I I 



I I 



i i i I i t i ! I i i i i — r 



j_i. 



1.- 1 1 ! 




1111 



Mill' 



J_i_ 



I I I 



■1 1... 



I 1. 



-15 



-10 



5 
ALPHA 



10 

CDEG) 



20 



25 



30 



T 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 107S.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB =■ 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP PITCH! 


NG MOMENT I 


SCR. 






-11.700 


0.02000 


0.02077 


0.01993 


0.01809 


0.02061 


. 02098 


0.02000 


0.02000 


-5.000 


0.01003 


0.01005 


0.00943 


0.00910 


0.01003 


0.01066 


0.01076 


0.01127 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01428 


-0.01314 


-0.01177 


-0.01311 


-0.01255 


-0.01467 


-0.01776 


-0.01928 


10.000 


-0 . 02963 


-0.02714 


-0.02431 


-0.02672 


-0 . 02669 


-0.03107 


-0 . 03559 


-0.04014 


16.300 


-0.04800 


-0 . 04493 


-0.04027 


-0.04389 


-0 . 04537 


-0.05223 


-0 . 05800 


-0 . 06500 


22.500 


-0.. 06500 


-0 . C6265 


-0.05618 


-0.06088 


-0 . 06455 


-0.07372 


-0 . 08000 


-O.OB800 



ENGINEER UJ*f£. 
OATE IKzJKrD 9 



FIGURE 4.1.1.3-43 

EFFECT OF BODY FLAP 



4.1.1.3-49 



c p "- . 



C J.. < 



ccec im 



'1* 



Rockwell International 

Spaca Division 



GO 

r 
u 

Q 



MACH NUMBER 



0.950 



DELBF CDEG) 

-25 25 

i i ! I | 1 i TT - ] 



-.06 



-.08 




CCtf I GURAT 


ON 




BASELINE ORB ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = F5 1076.7 IN. 


Wire AREA SW = 2690.00 


SQ.FT. 


OR YO • BL 0.0 IN. 


WING SPAN BW « 78.055 


FT. 


MOMENT REFERENCE 20 • W. 375.0 IN. 


M.A.C. CW ' 39.560 


FT. 




BOOY LENGTH LB = 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELBF (OEG) 


A 


B 


C 





E 


F 


G 


H 






BCOY 


FLAP PITCHI 


NG fOCNT I 


NCR. 






- 1 1 . 700 


0.03000 


0.02517 


0.02149 


0.01801 


0.01762 


0.02110 


0.02500 


. 02800 


-5.000 


0.01276 


0.01159 


0.01012 


. 00863 


0.00853 


0.00985 


0.01 121 


0.01233 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01262 


-0.01279 


-0.01280 


-0 . 1 078 


-0.01136 


-0.01091 


-0.01172 


-0.01265 


10.000 


-0.02512 


-0 . 02577 


-0 . 02602 


-0 . 02259 


-0.02361 


-0.02296 


-0.02387 


-0 . 02549 


16.300 


-o.omoo 


-0.04196 


-0. 0427 I 


-0 . 03783 


-0 . 03822 


-0.04085 


-0.04200 


-0.C4400 


22 . 500 


-0 . 05700 


-0 . 05773 


-0 . 05922 


-0.05319 


-0.05158 


-0.06224 


-0.06800 


-0.07400 



OATE XiisEriJe 



FIGURE 4.1.1.3-44 
EFFECT OF BODY FLAP 



4.1.1.3-50 



c r 



C . 



<w V 1 



M 



L 



fa 



Rockwell International 

Spacs Division 



MACH NUMBER 



0.980 



DELBF COEG) 

-25 25 



Ti i r 



.04 



.02 



00 

u 

Q 



.02 



.04 



-.06 



-.08 



.10 



I I I I 



I I I I 



I I L-L 



I I II I i I I i I l I 



Mil 




I I I I 



I I I I 



TT" 



I I I 



JL-L_L_L 



J- l I I 



I 1 



-15 



-10 



-5 



5 
ALPHA 



10 

CDEGD 



15 



20 



25 



30 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DlhCNSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN SW ' 78.056 FT. 


MGtENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 


H 






BCOY 


FLAP P1TCHI 


NG MOf-ENT I 


NCR. 






-11.700 


0.02849 


0.02495 


. 02072 


0.01803 


0.01741 


. 02097 


. 02444 


0.02736 


-5.000 


0.01207 


0.01106 


. 00978 


. 00B59 


0.00842 


0.00976 


0.01092 


0.01193 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.01181 


-0.01224 


-0.01272 


-0.01064 


-0.01131 


-0.01103 


-0.01140 


-0.01212 


10.000 


-0 . 02337 


-0.02468 


-0.02546 


-0.02224 


-0.02312 


-0.02326 


-0.02325 


-0.02435 


16.300 


-0.03822 


-0.04017 


-0.04149 


-0.03718 


-0.03755 


-0.04005 


-0.04047 


-0.04130 


22.500 


-0.05390 


-0 . 05524 


-0.C5726 


-0 . 05222 


-0.05132 


-0.05797 


-0.06255 


-0.06724 



ENGINEER U»*»l. 

0ATe.„3rj£gr5g 



FIGURE 4. 1. 1.3L45 

EFFECT OF BODY FLAP 



4.1.1.3-51 



M 



€* 



Rockwell International 

Space Division 



MACH NUMBER 



lo- 
rn 

o 



.04 



.02 



.0 



-.02 



-.04 



-.06 



-.08 



_L_Li 



I.1..I..1. 



050 
I i I i 



DELBF C0EG) 

-25 25 

I I I 1 i 



_L 



111! 




J_J_ 



I i i I 



_L-1_L_L 



! I i 



I I I I 



i I I T" 



T I I 



l I I I 



I I I I , 



■10 



5 

ALPHA 



to 
CDEG) 



15 



20 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = F5 1075.7 IN. 


WING AREA SW = 2590.00 SQ.FT. 


OR YO « 3L 0.0 IN. 


WING SPAN BW = 78.055 FT. 


MCfCNT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BCOY LENGTH L8 - 1290.3 IN. 



ENGINEER i~*i -Z_ 
DATE ZftZzXiZ- ~> & 



FIGURE 4.1.1.3-46 

EFFECT OF BODY FLAP 



30 











ALPHA 


<DEG> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELBF (C€G! 


A 


B 


c 





E 


F 


G 


H 






BCOY 


FLAP PITCHI 


NG MOENT I 


NCR. 






-11.700 


0.01472 


0.01531 


0.01574 


0.01831 


0.01889 


0.02017 


0.02154 


0.02235 


-5.000 


0.00730 


0.00762 


. 00785 


. 00870 


0.00897 


0.00937 


0.00983 


0.01012 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00929 


-0.01029 


-0.01051 


-0.01072 


-0.01138 


-0.01158 


-0.01115 


-0.01098 


10.000 


-0.01995 


-0.02154 


-0.02217 


-0.02239 


-0.02388 


-0.02363 


-0.02309 


-0.0228! 


16.300 


-0.03422 


-0.03596 


-0.03722 


-0.03742 


-0.03854 


-0.03839 


-0.03854 


-0.03882 


22.500 


-0.04903 


-0.05042 


-0.05241 


-0.05254 


-0.05138 


-0.05248 


-0 . 054 1 1 


-0.05575 



4.1.1.3-52 



C? : 



7;i-£:- 



CCCC 



M 



#1* 



Rockwall International 

Spaco Division 



!_ 



MACH NUMBER 



1. 100 



.04 



.02 



OELBK CDEGD 

-25 25 

| I I I I | I I I l"t 



U. 
CD 

z: 
u 

Q 



.0 



-.02 



.04 



.06 



-.08 



-.10 



TTT1 



I I I I 



J._L.l_J_JLl 



I I I 



_L.L_L 



TT'l 




I i i I I i I I i ~ 



L_L_L_L_L 



_L_L 



_LJ_ 



I ! ! 



I i I .1 



-15 



-10 



-5 



5 10 

ALPHA CDEG) 



15 



20 



30 



cor i guration 




BASELINE CR81TER VEHICLE 


REFERENCE DIt-ENSIONS 




CENTER OF GRAVITY XO = FS I07S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO ■ 3L 0.0 IN. 


WING SPAN BU - 78.056 


FT. 


MGf-ENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


<0EG> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OEL8F (DEG) 


A 


8 


c 





E 


F 


G 


H 






BOOY 


FLAP PITCH! 


NG MCfENT I 


NCR. 






-11-700 


0.00900 


0.01124 


0.01360 


0.01837 


0.CI918 


0.01941 


. 02000 


0.02000 


-5.000 


. 00527 


. 00607 


. 006S6 


. 00869 


. 00905 


. 00904 


0.00923 


0.00923 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00339 


-0 . 00877 


-0.00967 


-0.01064 


-0.01134 


-0.01102 


-0.01108 


-0.01108 


10.000 


-0.01850 


-0.01914 


-0.02054 


-0.02216 


-0 . 02375 


-0.02303 


-0.02300 


-0.02300 


16.300 


-0 . 03200 


-0.03298 


-0 . 03465 


-0.03698 


-0.03835 


-0.03720 


-0.03720 


-0.03720 


22.500 


-0.04600 


-0.04732 


-0 . 04894 


-0.C5I86 


-0.05121 


-0.04966 


-0.05000 


-0.05000 



ENGINEER W**J£ 

DATE "3zjkesD$ 



FIGURE 4.1.1.3-47 

EFFECT OF BODY FLAP 



4.1.1.3-53 



.M 



*1* 



Rockwell International 

Spaca Division 



MACH NUMBER 
■ pt> ' l I I I 



1.200 



DELBF COEG) 

-25 25 

I I I I I I I i I i I 



.05 



LL. 

00 

r 

CJ 
Q 



.02 



.04 



.06 



-.08 



-.io'i I I I I I 



TT 



TT 



I I I 



1 \T 




i i i i i i I i i n I ! i i 



.-15 



-10 



I 1 ! I I I I I I I I I I I -I I 
5 10 15 20 

ALPHA CDEG) 



iiii 



25 



30 



CONFIGURATION 




BASELINE 0RB1TER VEHICLE 


REFERENCE OireNSIONS 




CENTER CT GRAVITY XO - FS 107S.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


CR YO • BL 0.0 IN. 


WING SPAN BU » 78.056 


FT. 


MOMENT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DZG) 


A 


8 


.C 





E 


F 


G 


H 






BCOY 


FLAP PITCHI 


NG MCfENT I 


NCR. 






-11.700 


0.01000 


"0.01229 


0.01480 


0.01714 


0.01753 


0.01745 


0.01800 


0.01800 


-5.000 


0.00538 


0.00618 


0.00705 


0.00813 


0.00834 


0.00823 


. 0084 1 


0.00841 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00803 


-0.00835 


-0.00927 


-0.01029 


-0.01027 


-0.01031 


-0.01028 


-0.01018 


10.000 


-0.01716 


-0.01766 


-0.01878 


-0.02110 


-0.02148 


-0.02160 


-0.02164 


-0.02176 


16.300 


-0.02900 


-0.02971 


-0.03055 


-0.03481 


-0.03594 


-0.03487 


-0.03487 


-0.03487 


22.500 


-0.04100 


-0.04189 


-0.04195 


-0.04842 


-0.05051 


-0.04653 


-0 . 04600 


-0.04400 



ENGINEER 



k/*f ■ 



DATE l£"jlil34 



FIGURE 4.1.1.3-48 

EFFECT OF BODY FLAP 



4.1.1.3-54 



i l 



•OC-.C JM 



*I* 



Rockwell international 

Space Division j 



r 



MACH NUMBER 
■°^ lilt rTT-r 



1.300 



DELBF CDEGD 

25 25 

| I I t I | I ! IT 



Lo- 
rn 

u 

Q 



-.08 




CONFIGURATION 




BASELIbC 0R8ITER VEHICLE 


REFERENCE (MANSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW « 2690.00 


SQ.FT. 


OR YO ■ BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOENT REFERENCE 20 - M. 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB » [290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BODY 


FLAP PITCHI 


NG MOMENT I 


NCR. 






-11.700 


0.00700 


. 009H I 


0.01141 


0.01327 


0.01500 


0.01643 


0.01700 


0.01800 


-5.000 


0.00389 


0.00492 


0.00568 


0.00660 


0.00763 


0.00809 


0.00824 


0.00864 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00525 


-0 . 00764 


-0.00807 


-0.00920 


-0.01081 


-0.01081 


-0.01077 


-0.01106 


10.000 


-0.01184 


-0.01545 


-0.01638 


-0.01927 


-0.02341 


-0.02338 


-0 . 02305 


-0 . 02369 


16.300 


-0.02200 


-0 . 02530 


-0.02686 


-0.03114 


-0.03750 


-0.03742 


-0.03700 


-0 . 03800 


22.500 


-0.03400 


-0-03502 


-0 . 03722 


-0.04183 


-0.04837 


-0.04774 


-0.04800 


-0.04900 



ENGINEER vw*»T_ 
DATE ZZSrZIZ*-"* * 



FIGURE 4.1.1.3-49 
, EFFECT OF BODY FLAP 



4.1.1.3-55 



iM 



*i* 



Rockwell International 

Spac* Division 



MACH NUMBER 
■ <* r-rrrrrm 



.02 



: ^z-^z±^:r^ 



ca 

o 
o 



-.02 



-.04 



-.06 



-.08 



-.10 



_L.I I. I 



I I ,1 I 



1.500 
i i i | i i i I i I I l l 



DELBF CDEG) 

-25 25 

I I I I I I I I i I 




J_L 



J_J_ 



-I..1 



I I I | I t I I ' 



I I 




1 I I I 



TTT 



I I I 1 



i I I I 



--~\ 



III! 



-15 



■10 



5 

ALPHA 



10 

CDEGD 



15 



20 



25 



30 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO ■ BL 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MCfENT REFERENCE ZO = UL 375.0 IN. 


M.A.C. CW = 39.550 FT. 




BCOY LENGTH LB = 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (OEG) 


A 


B 


C 





E 


F 


G 


H 






BCOY 


FLAP P1TCHI 


NG MOMENT I 


NCR. 






-11.700 


0.00858 


0.00914 


0.00981 


0.01073 


0.01212 


0.01627 


0.01849 


0.02159 


-5.000 


0.00423 


0.00451 


. 00489 


. 00543 


0.00617 


0.00767 


. 00846 


0.00962 


0-0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00598 


-0.00620 


-0.00670 


-0 . 00764 


-0.00877 


-0.00951 


-0 . 00998 


-0.01060 


10.000 


-0.01202 


-0.01292 


-0.01448 


-0.01650 


-0.01895 


-0.02017 


-0 . 02060 


-0.02198 


16.300 


-0.01963 


-0.02091 


-0.02319 


-0.02545 


-0.03037 


-0.03244 


-0 . 03337 


-0 . 03549 


22.500 


-0.02713 


-0.02821 


-0 . 02979 


-0.03424 


-0.03929 


-0 . 04229 


-0.04509 


-0 . 04674 



ENGINEER l*±*2X. 
DATE J3_-55E;'"> * 



FIGURE 4.1.1.3-50 

EFFECT CF BODY FLAP 



4.1.1.3-56 



ID 



H -uCtiC IM 




Rockweil /international 

Space Division 



J— 



MACH NUMBER 



2.000 



DELBF COEG) 

-25 25 

1 rTTT" 



u. 

CD 




5 10 15 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE 0!^€^JS!ONS 


CENTER OF GRAVITY XO • FS 1076.7 IN. 


UING AREA SU » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU = 78.056 FT. 


M>£NT REFERENCE ZO » UI_ 375.0 IN. 


M.A.C. CU - 39.560 FT. 




BCCY LENGTH LB » 1290.3 IN. 







ALPHA (C€G> 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


30 . 000 


DELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 


1 








BCOY FLAP PITCHING MOM 


ENT I NCR. 








-11.700 


0.00400 


0.00570 


0.00578 


0.00705 


0.00909 


0.01125 


0.01324 


0.01334 


0.01534 


-5.000 


0.00211 


0.00291 


0.00297 


0.00360 


0.00452 


0.00540 


0.00636 


0.00576 


0.00778 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00261 


-0.00331 


-0.00403 


-0.00531 


-0.00637 


-0.00709 


-0.00736 


-0 . 00823 


-0.00937 


10.000 


-0.00575 


-0.00715 


-0 . 00857 


-0.01101 


-0.01320 


-0.01467 


-0.01575 


-0.01799 


-0.02044 


16.300 


-0.01100 


-0.01300 


-0.01481 


-0.01784 


-0.02138 


-0.02377 


-0.02800 


-0.03300 


-0.03800 


22.500 


-0.01800 


-0.02000 


-0.02112 


-0.024 16 


-0 . 02897 


-0.03221 


-0.04200 


-0.05100 


-0.06000 



EKSlr££R U> ^*- 
DATE I3jfE5?>8 



FIGURE 4.1.1.3-51 
EFFECT OF BODY FLAP 



4.1.1.3-57 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 



3.000 



.cm 



.02 



u. 

CO 

z: 
a 
a 



-.02 



.04 



-.06 



-.08 



DELBF CDEG) 

-25 25 

| I ! i I | I i I I | 



! i I ! I I I I I I i I i i 



■ A » 



.10 
-15 




-LI I, 1 



I I I I 



■• rF^S. 



I I I 



TTT 



: = =fa C 4=ag;=^; ;-- 



I 



r 'it r r 



i I i ii 



^ 




JL-L 



1 




l l I l 



l l l 



-10 



5 

ALPHA 



10 

CDEG) 



15 



20 



1 .1 1 i. 



25 



30 



CONFIGURATION 




BASELINE CR8ITER VEHICLE 


REFERENCE DirtNSIONS 




CENTER OF GRAVITY XO « FS 1076.7 IN. 


WING AREA SW « 2690.00 


SQ.FT. 


OR YO = BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOENT REFERENCE 20 • WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB = 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (0EG) 


A 


B 


C 





E 


F 


G 


H 






BODY 


FLAP PITCH! 


NG MCttNT ! 


<R. 






-11.700 


. 00006 


0.00180 


. 00265 


0.00375 


. 00490 


0.00559 


0.00850 


0.01137 


-5.000 


0.0004 i 


0.00110 


0.00148 


0.00198 


0.00253 


0.00353 


0.00447 


. 00575 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00143 


-0.00186 


-0.00233 


-0.00292 


-0.00416 


-0.00542 


-0.00671 


-0.00849 


10.000 


-0.00313 


-0 . 00408 


-0.00499 


-0.00618 


-0.00857 


-0.01118 


-0.01398 


-0.01710 


16.300 


-0.00530 


-0.00700 


-0.00842 


-0.01037 


-0.01416 


-0.01849 


-0.02324 


-0.02795 


22.500 


.-0.00750 


-0.01000 


-0.01189 


-0.01459 


-0.01971 


-0.02575 


-0.03248 


-0 . 03865 



ENGINEER **>S?lz 
DATE ZK'JiAzIS 



FIGURE 4.1.1.3-52 

EFFECT OF BODY FLAP 



4.1.1.3-58 



-CCC C 1M 



Ijl 



Rockwell International 

Space Division 



MACH NUMBER 



.OH 



.02 



u. 

CO 

8 



-.02 



-.04 



.06 



-.08 



i I I I I I I I 



10' ' ' I I 



-LI I I 1 



3.000 
"i l i rr 



DELBF CDEG) 

-25 25 

| I I I I 



I I I 1 I I 



Till 




I I I I I ! I I I 



I I I 



1 I I 



i i r 



10 



15 



20 25 30 35 

ALPHA CDEG3 



HO 



H5 



50 



CONFIGURATION 




BASELINE CR8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


UING AREA SW « 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB = 1290.3 


IN. 





ALPHA (OEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELBF (OEG) 


F 


G 


H 


I 


J 


K 


L 






BCOY FLAP PITCHING MOM 


ENT I NCR. 






- 1 1 . 700 


0.00669 


0.00850 


0.01137 


0.01350 


0.01550 


0.01800 


0.02000 


-5.000 


0.00353 


0.00447 


. 00575 


0.00677 


0.00775 


0.00890 


0.00988 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00542 


-0.00671 


-0.00849 


-O. 00981 


-0.01131 


-0.01250 


-0.01390 


10.000 


-0.01118 


-0.01398 


-0.01710 


-0 . 02000 


-0.02271 


-0.02551 


-0.02830 


16.300 


-0.01849 


-0.0232H 


-0.02795 


-0.03250 


-0.03700 


-0.0H150 


-0.04600 


22.500 


-0.02575 


-0.03248 


-0 . 03865 


-0.04450 


-0.05100 


-0.05700 


-0 . 06300 



ENGINEER V*>MZ. 
DATE j5-3$!="7* 



FIGURE 4.1.1.3-53 
EFFECT OF BODY FLAP 



4.1.1.3-59 



r r t <~ c 



J-L- /2-Lri-CCeC IM 



'1* 



Rockwell International 

Space Division 

L 



MACH NUMBER = 4.000 

-°*\ l l I I I I I I i I i i i i I i i i i I i 



DELBF CDEG3 

-25 25 



| I I I I 



.02 



a 



.02 



-.04 



-.06 



-.08 



.10 



A A > A ' »c L sg r 



■Jill 



'Ns^fS^gg 



I I I I 



1, I, I. .1 



I I 1 I 



mi r 



JL 



_L 



I ! I 




Ml! 



I I I 
I I I 



M i l 



I I I I 



M il 



■15 



-10 



5 
ALPHA 



10 

CDEG) 



15 



20 



25 



30 



CONFIGURATION 




BASEL !N£ 0R8ITER VEHICLE 


REFERENCE Oir-ENSICNS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCt-ENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. Ol » 39.550 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (DEG) 


A 


8 


c 


O 


E 


F 


G 


H 






BCOY 


FLAP PITCH! 


NG MOf-CNT I 


gCR. 






-11.700 


0.0 


0.00030 


0.00115 


0.00150 


0.00255 


0.00420 


0.00603 


. 00830 


-5.000 


0.00014 


0.00032 


0.00074 


0.00106 


0.00169 


0.00261 


0.00365 


. 00480 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00028 


-0.00052 


-0.00100 


-0.00156 


-0 . 00249 


-0.00396 


-0.00619 


-0.00875 


10.000 


-0.00069 


-0.00123 


-0.00225 


-0 . 00365 


-0.00584 


-0.00915 


-0.01349 


-0.01763 


16.300 


-0.00195 


-0 . 00305 


-0.00495 


-0.00781 


-0. .01 175 


-0.01702 


-0 . 02304 


-0.02870 


22.500 


-0. 00420 


-0.00590 


-0.00890 


-0.01250 


-0.01720 


-0.02400 


-0.03280 


-0 . 04260 



ENGINEER -^kD* 

DATE_wQ.rl"f£rir}5 



FIGURE 4.1.1.3-54 

EFFECT OF BOOY FLAP 



4.1.1.3-60 



"/2-cH- CCC C JM 



* 



Rockwell International 

Spec* Division 



MACH NUMBER 



.04 



.02 



u. 



u 

Q 



.02 



.04 



.06 



.08 



-.10 



i i r 



i i i i 



1 I IT 



i I 



4.000 
I l I l 



DELBF CDEG3 

-25 25 

I I I I I 




I I I I I 



^H 



I I I I 



- 1 I I 




.II IL 



I I I I 



J_±. 



10 



15 



SO 



25 30 

ALPHA CDEGD 



35 



HO 



45 



50 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW « 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CU * 39.560 


FT. 




BODY LENGTH LB - 1290.3 ■ 


IN. 





ALPHA (OEG) 


15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


OELBF (DEG) 


F 


G 


H 


I 


J 


K 


L 






BODY FLAP PITCHING MOM 


ENT [NCR. 






-11.700 


0.00420 


0.0C603 


0.00830 


0.01075 


0.01335 


0.01606 


0.01886 


-5.000 


0.00261 


0.00365 


. 00480 


0.00604 


. 00737 


0.00866 


. 00973 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00396 


-0.00619 


-0.00875 


-0.01000 


-0.01163 


-0.01309 


-0.01380 


10.000 


-0.00915 


-0.01349 


-0.01763 


-0.02181 


-0.02599 


-0.02961 


-0.03100 


16-300 


-0.01702 


-0.02304 


-0.02970 


-0 . 03470 


-0.04130 


-0.04679 


-0.04900 


22.500 


-0.02400 


-0.03280 


-0.04260 


-0 . 04930 


-0.05260 


-0.05460 


-0.05625 



ENGINEER J^C* 

DATE__ > _ < 5rji5_r-ri5> 



FIGURE 4.1.1.3-55 
EFFECT OF BODY FLAP 



4.1.1.3-61 



sz ?2-s::-ccec im 



€> 



Rockwell International 

Space Division 



MACH NUMBER 
.04 



5.000 



DELBF CDEG3 

-25 25 

I I I I I I I I I ! I 



.02 



g 



-.02 



.OH 



-.06 



.08 



.10 



Jill 


i i i i 


111! 


rrrr 


III! 


ill! 


iiil 


till 


1 1 1 i 


h * 




^ r^ /-..- _£•___ 


tottrr-®—&-'' 


-=s^§'~ Ss - ; 




= -^Sk; 


==*^ 








^yiyssigj 






"""^-^ 


?^\- 




— \i 


- 


~ 












~-F. 


"^ 


~"~-— \ 


t - 


- 


















""-k 


_ 




III! 












: 


: 

1 1 r 


i i i i 


111! 


1 1 1 I 


I I I > 


i i i. i 


i i i i 


! 1 1 !~ 



-15 



-10 



5 

ALPHA 



to 
CDEGD 



15 



20 



25 



30 



CONFIGURATION 


BASELINE 0R8ITER VEHICLE 


REFERENCE DIfENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU - 2690.00 SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


rt»€NT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BCOY LENGTH LB • 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


0ELBF (OEG> 


A 


B 


c 


D 


E 


F 


G 


H 






BCOY 


FLAP PITCH I 


NG MOMENT I 


SCR. 






-11.700 


0.0 


0.00010 


0.00020 


0.00080 


0.00160 


0.003m 


0.00538 


0.00791 


-5.0C0 


0.00007 


0.00014 


0.00027 


0.00067 


0.00123 


0.0021'+ 


0.00333 


0.00465 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00013 


-0.00022 


-0.00045 


-0.00105 


-0.00194 


-0.00330 


-0 . 00497 


-0 . 00702 


10.000 


-0.00030 


-0.00052 


-0.00107 


-0.00249 


-0.00463 


-0.00777 


-0. 01148 


-0.01584 


16.300 


-0.00090 


-o.oo mo 


-0.00275 


-0.00560 


-0.00967 


-0.01520 


-0.02150 


-0 . 02930 


22.500 


-0 . 00270 


-0.00380 


-0.00660 


-0.01030 


-0.01510 


-0 . 02250 


-0 . 03320 


-0 . 04420 



ENGINEER JXȣ> 
OATE__LQ2C5IrZI5 



FIGURE 4.1.1.3-56 

EFFECT OF BODY FLAP 



^~/ 



4.1.1.3-62 



-L; :-ov -C iM 



4* 



Rockwell International 

Spac#Drvwtoo 



MACH NUMBER 



5.000 



DELBF CDEG) 

-25 25 



.04 



.02 



t~t 



.02 



.04 



-.06 



-.08 



-.10 



I I I I I 



! I I I 



I I i I 



I I I I I I 



I I I 



_L_L 



m I i i i i r i 




-L_L 



l I l I 



i I I i 



I I I 



I I I 1 | 
III! 



J-JL 



10 



15 



20 



25 



30 

ALPHA 



35 
CDEGD 



40 



45 



50 



55 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO • 8L 0.0 IN. 


UING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO > WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH L8 - 1290.3 


IN. 











ALPHA 


(DEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELBF tOEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP P1TCHI 


NG MOMENT I 


NCR. 






-11.700 


0.00314 


0.00538 


0.00791 


0.01062 


0.01362 


0.01662 


0.01962 


0.02262 


-5.000 


0.00214 


0.00333 


0.00465 


0.00600 


0.00740 


0.00874 


0.00S96 


0.01094 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00330 


-0.00497 


-0.00702 


-0.00955 


-0.01192 


-0.01296 


-0.01385 


-0.01405 


10.000 


-0.00777 


-0.01148 


-0.01584 


-0.02050 


-0.02507 


-0.02852 


-0.03069 


-0.03062 


16.300 


-0.01520 


-0.02150 


-0.02830 


-0.03470 


-0.04050 


-0.04550 


-0.04875 


-0.04880 


22.500 


-0.02250 


-0.03320 


-0.. 04420 


-0.05220 


-0.05520. 


-0 . 05730 


-0.05880 


-0.05950 



ENGINEER £6D 
0ATE._'O.rS?r?!35 



FIGURE 4.1.1.3- 57 
__ EFFECT OF BODY FLAP 



4.1.1.3-63 



£D 



72-SH-0C6C 1M 



^1^ 



Rockwell International 

Space Division 



MACH NUMBER 



8. 000 



OELBh CDEGD 
-as 25 

III!) 



m 

Q 




5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORB ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BU 0.0 IN. 

MONENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DINENSIONS 
WING AREA SW = 2690.00 SQ.FT. 
WING SPAN SW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB * 1290.3 IN. 











ALPHA 


(OGG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


C€L8F (C€G) 


A 


B 


c 





E 


F 


G 


H 






BCOY 


FLAP PITCH! 


NG M>ENT I 


NCR. 






-11.700 


0.0 


0.00044 


0.00088 


0.00137 


0.00198 


0.00280 


. 00398 


0.00639 


-5.000 


. 00004 


0.00022 


0.00043 


0.00071 


0.00110 


0.00170 


. 00267 


0.00417 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00007 


-0 . 00024 


-0 . 00048 


-0.00083 


-0.00136 


-0.00229 


-0 . 00403 


-0 . 00632 


10. COO 


-0.00016 


-0 . 00049 


-0.00099 


-0.00175 


-0.002S8 


-0 . 00520 


-0.00948 


-0.01479 


16.300 


-0.00050 


-0.00100 


-0.00200 


-0.00360 


-0 . 00620 


-0.01080 


-0.01875 


-0 . 02850 


22.500 


-0.00170 


-0.00300 


-0 . 00490 


-0.00750 


-0.01200 


-0.01950 


-0 . 03070 


-0.04530 



ENGINEER U*y«-U 
DATE ZZ^ZilLi ""?* 



FIGURE 4.1.1.3-58 
EFFECT OF BODY FLAP 



4.1.1.3-64 



SC 72-EH-OCeC 1IVI 



€ 



Rockwell International 

Space Civision 






MACH NUMBER 



8.000 



DELBF CDECO 

"25 £5 



o 
a 




30 35 

ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

CR YO « BL 0.0 IN. 

MCfrENT REFERENCE 20 « UC 375.0 IN. 



REFERENCE OlhCNSICNS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

SCOY LENGTH LB = 1290.3 IN. 











ALPHA 


(C€G! 






15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50.000 


OELBF (D€G) 


F 


G 


H 


I 


J 


K 


L 


M 






BODY 


FLAP PITCH! 


NG h>ENT I NCR. 






-11.700 


0.00280 


0.00398 


0.00639 


0.00910 


0.01200 


0.01510 


0.01830 


0.02160 


-5.000 


0.00170 


0.00267 


0.00417 


0.00556 


0.00691 


0.00829 


0.00952 


0.01093 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00229 


-0.00403 


-0.00632 


-0.00813 


-0.01009 


-0.01274 


-0.01483 


-0.01538 


10.000 


-0.00520 


-0.00948 


-0.01479 


-0.01877 


-0.02279 


-0.02724 


-0.03089 


-0.03327 


16.300 


-0.01080 


-0.01875 


-0.02850 


-0.03550 


-0.04100 


-0.04600 


-0.05000 


-0.05330 


22.500 


-0.01950 


-0.03070 


-0.04530 


-0 . 05550 


-0.06100 


-0.06500 


-0.06760 


-0.06870 



ENGINEER Ui*7_ 
OATE ~5?-V&Z "7 3 



FIGURE 4.1.1.3-59 
EFFECT OF BODY FLAP 



4.1.1.3-65 



c n -r 



D 72-SH-CCec 1M 



'i* 



Rockwell International 

Space Division 



MACH NUMBER = 10.000 

■^i I I I II I I I ( |'l I 1 I M'l i l| I 



DELBF CDEGD 

-25 25 

| I I I I | I I I i | 



.02 



Ll 

2: 
u 
o 



-.02 



-.04 



.06 



-.08 



.10 



+- +- s a AB» g Jw3 Jl< " !ij!^| gg^^^^ 



I I 



I I I 



I 1 I I 



I I I 



III ! 



I I i I I I 




1 I I I 



~m 



llll 



-15 



-10 



5 

ALPHA 



10 

CDEG) 



15 



20 



25 



30 



CONFIGURATION 


BASELINE ORBtTER VEHICLE 


REFERENCE OI^NSIONS 


CENTER Of GRAVITY XO • FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING 5PAN BH - 78.056 FT. 


MCfCNT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


<D£G) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 


H 






BCOY 


FLAP PITCH I 


NG MOtENT I 


MCR. 






-11.700 


0.0 


0.00054 


0.00098 


0.00138 


0.00178 


0.00269 


0.00408 


0.00641 


-5-000 


0.00001 


0.00024 


0.00047 


0.00072 


0.00103 


0.00162 


0.00251 


0.00414 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00003 


-0.0002H 


-0.00051 


-0.00084 


-0.00132 


-0.00213 


-0.00343 


-0.00616 


10.000 


-0.00006 


-0.00049 


-0.00105 


-0.00179 


-0.00293 


-0.00479 


-0.00786 


-0.01438 


16.300 


-0.00020 


-0.00086 


-0.00200 


-0.00366 


-0.00617 


-0.01015 


-0.01610 


-0.02800 


22.500 


-0 . 00070 


-0 . 00292 


-0 . 003S0 


-0.00746 


-0.01180 


-0.01922 


-0.02820 


-0.04510 



ENGINEER <-"*T_ 
DATE Z?££%Z°~.~>* 



FIGURE 4.1.1.3-60 

EFFECT GF BODY FLAP 



4.1.1.3-66 




Rockwell International 
SpacaDtwsicn 



MACH NUMBER 



10.000 



.04 



.02 



DELBF CDEG) 

25 O 25 



u. 

CD 

u 
o 



.02 



.04 



.06 



.08 



-.10 



i i i I i i i i r r 



_L_L 



TTT" 



.1 1 L 



I I I I I I 



I I I i I I I I I I I I 




. 1 1 LI 



-m~r 



—=^*L 



TTT 



T i IT" 



10 



15 



20 25 30 35 

ALPHA CDEG) 



J....I I I 



40 



45 



50 



55 



CONFIGURATION 


BASELINE ORB1TER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW • 2690.00 SQ.FT. 


OR YO ' bl 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW » 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


<C€G) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


OELBF CDEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP PITCHI 


NG MOMENT I 


NCR. 






-11.700 


0.00269 


0.00408 


0.00641 


0.01005 


0.01205 


0.01500 


0.01804 


0.02180 


-5.000 


0.00162 


0.00251 


0.00414 


0.00587 


0.OC692 


0.00818 


0.00958 


0. 01111 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00213 


-0.00343 


-0.00616 


-0.00825 


-0.01004 


-0.01178 


-0.01485 


-0.01567 


10.000 


-0.00479 


-0.00786 


-0.01438 


-0.01886 


-0.02258 


-0.02590 


-0.03135 


-0.03434 


16.300 


-0.01015 


-0.01610 


-0.02800 


-0.03550 


-0.04090 


-0.04500 


-0.05060 


-0.05480 


22.500 


-0.01922 


-0.02820 


-0.04510 


-0.05540 


-0.06100 


-0.06500 


-0.06770 


-0.06680 



ENGINEER Sowl. 
OATE I33sX£3 ") % 



FIGURE 4.1.1.3-61 

EFFECT OF BODY FLAP 



4.1.1.3-67 



SD72-SH-0Cec 1M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER = 15.000 

• w ' I I I I I I I 'I I I ( I I I 



DELBF CDEG) 

-25 25 

till 



u. 

H 

u 
a 




10 

CDEG3 



CONFIGURATION 




BASELINE ORB ITER VEHICLE 


REFERENCE OI^£NSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOtENT REFERENCE ZO • U. 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (C€G) 


A 


B 


c 





E 


F 


G 


H 






BCOY 


FLAP PITCHI 


NG MOttNT I 


NCR. 






-11.700 


0.0 


0.00054 


0.00098 


0.00138 


0.00178 


. 00269 


0.00408 


0.00641 


-5.000 


0.00001 


. 00024 


0.00047 


0.00072 


0.00103 


0.00162 


0.00251 


0.00414 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00003 


-0 . 00024 


-0.00051 


-0 . 00084 


-0.00132 


-0.00213 


-0.00343 


-0.00616 


10.000 


-0.00006 


-0.00049 


-0.00105 


-0.00179 


-0.00293 


-0.00479 


-0.00786 


-0.01438 


16.300 


-0.00020 


-0.00086 


-0 . 00200 


-0.00366 


-0.00617 


-0.01015 


-0.01610 


-0.02800 


22.500 


-0.00070 


-0 . 00292 


-0 . 00390 


-0 . 00746 


-0.0! 180 


-0.01922 


-0 . 02820 


-0.04510 



ENGINEER Wj *"> i- 
DATE "5;3Z€ "11 



FIGURE 4.1.1.3-62 

EFFECT OF BODY FLAP 



4.1.1.3-68 



V-/ 



SD 72 -3H-CI ec irvi 



'1* 



Rockwell International 

Space Division 



OELBF (DEGD 

25 25 

I I I I 



u. 

m 

y 

G 

o 




30 35 

ALPHA CDEGD 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIf-ENSIONS 


CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW » 78.056 FT. 


MOCNT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CM - 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 











ALPHA 


(C€G) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


CGLBF (CEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BOOY 


FLAP PITCH I 


NG MCf€NT I 


NCR. 






-11.700 


0.00269 


0.00408 


0.00641 


0.01005 


0.01205 


0.01500 


0.01804 


0.02180 


-5.000 


0.00162 


0.00251 


0.00414 


0.00587 


0.00592 


0.00818 


0.00958 


0.01111 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00213 


-0 . 00343 


-0.00616 


-0.00825 


-0.01004 


-0.01178 


-0.01485 


-0.01567 


10.000 


-0.00479 


-0.00786 


-0.01438 


-0.01886 


-0.02268 


-0.02590 


-0.03135 


-0.03434 


16.300 


-0.01015 


-0.01610 


-0.02800 


-0.03550 


-0.04090 


-0.04500 


-0.05060 


-0.054S0 


22.500 


-0.01922 


-0.02820 


-0.04510 


-0.05540 


-0.06100 


-0.06500 


-0.06770 


-0.06880 



ENGINEER >JMT- 
DATE Zj£\OjQg 



FIGURE 4.1.1.3-63 

EFFECT OF BODY FLAP 



4.1.1.3-69 



SD7 2-SH-CCCC 1M 



* 



Rockwell International 

Space Division 



03 
2: 
<_) 
Q 



MACH NUMBER 
■O^r 1 1 i 1 



.02 



.02 



.04 



.06 



.08 



4r- \ A ABa B J^ ! 



IqL I M 1, 1 1 



20.000 
1 1 1 1 1 1 i 1 1 1 1 1 1 1 1 1 r 



DELBF CDEGD 

-25 25 

I I 1 I I I I I I 1 ) 



1 . 1. 1 1 



I I I 



n r~; rr~ 1 r~n r~i r~i 1 r~r 




_L_L 



1 1 1 



j_j_ 



1 1 i 1 



•15 



-10 



5 10 

ALPHA CDEG: 



15 



20 



25 



30 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 1076.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO « BL 0.0 IN. 


WING SPAN 8W = 78.056 


FT. 


MOMENT REFERENCE ZO * UL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB * 1290.3 


IN. 











ALPHA 


<C€G) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (CEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP PITCHI 


NG MCt-ENT I 


NCR. 






-11.700 


0.0 


0.00054 


0.00098 


0.00138 


0.00178 


0.00269 


0.00408 


0.00541 


-5.000 


0.00001 


0.00024 


0.00047 


0.00072 


0.00103 


0.00162 


0.00251 


0.00414 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00003 


-0.00024 


-0.00051 


-0.00084 


-0.00132 


-0.00213 


-0.00343 


-0.00616 


10.000 


-0-00006 


-0.00049 


-0.00105 


-0.00179 


-0.00293 


-0.00479 


-0.00786 


-0.01438 


16.300 


-0.00020 


-0.00086 


-0.00200 


-0.00366 


-0.0C517 


-0.01015 


-0.01610 


-0 . 02800 


22.500 


-0.00070 


-0.00292 


-0.00390 


-0.00746 


-0.01180 


-0.01922 


-0.02820 


-0.04510 



ENGINEER Wi"X- 
DATE IKr-VP--'?^ 



FIGURE 4.1.1.3-64 

EFFECT OF BODY FLAP 



4.1.1.3-70 



'1* 



Rockwell International 
Space Division 



MACH NUMBER 



20.000 



^DELBF CDEG) 

-25 25 



u. 

CO 

o 
o 



-.06 



-.08 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO » FS 1076.7 IN. 

CR YO - BL 0.0 IN. 

MOMENT REFERENCE 20 = W_ 375.0 IN. 



REFERENCE DI«>6IONS 
WING AREA SW » 2690.00 SQ.FT. 
UING SPAN BW = 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB = 1290.3 IN. 



DELBF (OEG) 



-11.700 
-5.000 
0.0 
5.000 
10.000 
16.300 
52.500 



15.000 

F 



20.000 
G 



ALPHA (OEG) 



25.000 
H 



30.000 
I 



35.000 
J 



40.000 
K 



45.000 

L 



0.00269 
0.00162 
0.0 
-0.00213 
-0.00479 
-0.01015 
-0.01922 



0.00408 
0.00251 
0.0 
-0.00343 
-0.00786 
-0.01610 
-0 . 02820 



80DY FLAP PITCHING MOMENT (NCR. 



50 . 000 
M 



0.00641 
0.00414 
0.0 
-0.006 IS 
-0.01438 
-0.02800 
-0.04510 



0.01005 
0.00587 
0.0 
-0 . 00825 
-0.01886 
-0.03550 
-0.05540 



0.01205 


0.01500 


0.01804 


0.02180 


0.00692 


0.00818 


0.00958 


0.01 111 


0.0 


0.0 


0.0 


0.0 


-0.01004 


-0.01178 


-0.01485 


-0.01567 


-0.02268 


-0.02590 


-0.03135 


-0.03434 


-0.04090 


-0 . 04500 


-0.05060 


-0 . 05480 


-0.06100 


-0 . 06500 


-0.06770 


-0.06880 



ENGINEER WMV 
DATE ZJ5H5S " 7 * 



FIGURE 4.1.1.3-65 
EFFECT OF BODY FLAP 



4.1.1.3-71 



SD72-£H-0CeC Jm 



«L* 



Rockwell International 

Space Division 



VBAR 
.04f— r-r— tt 



0.005 



DELBF CDEG) 

-25 25 



CD 

a 




-.06 



ALPHA CDEGD 



CONF IGURATION 



BASELINE ORBITER VEHICLE 
CENTER Cf GRAVITY XO = FS 1076.7 IN. 
OR YO * BL 0.0 IN. 

MCf-CNT REFERENCE ZO - UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 2690-00 SQ.FT. 
WING SPAN BW * 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB - 1290.3 IN. 





ALPHA (OEG) 








20.000 
A 


25.000 
S 


30 . 000 
C 


35.000 
D 


40.000 

E 


45.000 

F 


50 . 000 
G 


<OEG> 






BODY FLAP PITCHING MCH 


ENT COEFFI 






1 1 . 700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 


0.00408 
0.00174 
0.0 
-0.00548 
-0.01096 
-0.01610 
-0.02820 


0.00641 
. 00274 
0.0 
-0 . 00848 
-0.01695 
-0.02800 
-0.04510 


. 1 005 
0.00429 
0.0 
-0.01083 
-0.02164 
-0.03550 
-0 . 05540 


0.01205 
■ . 005B3 
0.0 
-0.01226 
-0.02453 
-0.04090 
-0.06100 


0.01500 
0.00703 
0.0 
-0.01342 
-0.02685 
-0 . 04500 
-0 . 06500 


0.01804 
. 00839 
0.0 
-0.01460 
-0.02921 
-0 . 05060 
-0 . C6770 


0.02180 
0.00968 
0.0 
-0.01539 
-0 . 03077 
-0 . 05480 
-0.06880 



ENGINEER 
DATE 



NASA 



FIGURE 4.1.1.3-66 

EFFECT OF BODY FLAP 



4.1.1.3-72 



'i* 



Rockwell International 
Space Division 



VBAR 



0.010 



DELBF CDEG] 

-25 25 



U. 

ca 

CJ 

c 



-.06 



-.08 




30 35 MO 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 107S.7 IN. 

OR YO - SL 0.0 IN. 

MOMENT REFERENCE ZO » U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW « 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1290.3 IN. 







ALPHA (OEG) 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


OELBF (OEG) 


A 


B 


C 





E 


F 


G 






BCOY FLAP PITCHING MOM 


ENT COEFFI 






-11.700 


. 00408 


. 0064 1 


0.01005 


0.01205 


0. 01 500 


0.01804 


0.02180 


-5.000 


0.00174 


. 00274 


0.00429 


0.00583 


. 00703 


0.00839 


0.00968 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00548 


-0.00848 


-0.01083 


-0.01226 


-0.01342 


-0.01460 


-0.01539 


1 . 000 


-0.01096 


-0.01695 


-0.02164 


-0.02453 


-0.02685 


-0.02921 


-0.03077 


16.300 


-0.01610 


-C . 02800 


-0.03550 


-0.04090 


-0 . 04500 


-0.05060 


-0 . 05480 


22.500 


-0 . 02820 


-0.04510 


-0 . 05540 


-0.06100 


-0 . 06500 


-0 . 06770 


-0 . 06880 



ENGINEER_N A SA 
DATE ""I 



FIGURE 4.1.1.3-67 
EFFECT OF BODY FLAP 



4.1.1.3-73 



SD72-SK-CCeC 1M 



* 



Rockwell International 

Space Division 



VBAR 



0.020 



a 



.04 



.02 



.0 



-.02 



-.OH 



-.06 



i i l 



-.08 



r i i i i 1 i 



i i i i r 



i i i i i i 




DELBF CDEG) 

-25 25 

| I I I I | i I I I ( 

I I 'I ! I 1 I I I I 



--S 



I I I I I I I I I I I I I 1 I .1 L 



I I I I 1 I I 



15 



20 



25 



30 35 40 

ALPHA CDEG) 



45 



50 



55 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OT GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO ■ BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO « U. 375.0 IN. 


M.A.C. CW ' 39.560 


FT. 




BOOY LENGTH L8 ' 1290.3 


IN. 





ALPHA (DEG) 




20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50 . 000 


DELBF (DEC) 


A 


8 


C 





E 


F 


G 


BODY FLAP PITCHING MGttNT COEFFI 




-11.700 


0.00408 


0.00641 


0.01005 


0.01205 


0.01500 


0.01804 


0.02180 


-5.000 


0.00174 


. 00274 


0.00429 


. 00583 


0.00703 


0.00839 


0.00968 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00548 


-0.00848 


-0.01083 


-0.01225 


-0.01342 


-0.01460 


-0.01539 


10.000 


-0.01096 


-0.01695 


-0.02164 


-0.02453 


-0.02685 


-0.02921 


-0.03077 


16.300 


-0.01740 


-C. 02640 


-0.03370 


-0.03980 


-0.04400 


-0.04740 


-0.05050 


22.500 


-0.02820 


-0.04510 


-0.05540 


-0.06100 


-0.06500 


-0.06770 


-0 . C6880 



ENGINEER NASA 
DATE """ 



FIGURE 4.1.1.3-68 

EFFECT OF BODY FLAP 



h. 1.1. 3-74 



CL12-S : ,-CCtC i(Vi 



'1* 



Rockwell International 

Space Division 



DELBF CDEG) 
-25 o as 

i i I i — i i i 







-.06 



35 40 

ALPHA CDEGD 



55 



CONFIGURATION 



BASELIhC 0R9ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO = BL 0.0 IN. 

MOMENT REFERENCE ZO = UL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW = 3690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BOOY LENGTH LB " 1290.3 IN. 



DELBF (OEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



ALPHA (CEG) 



20.000 
A 



25.000 
8 



30 . 000 

c 



35.000 
D 



HO. 000 
. E 



45.000 

F 



50 . 000 
G 



BOOY FLAP PITCHING MOMENT COEFFI 



0.00400 
0.00290 
0.0 
-0.00350 
-0.00800 
-0.01530 
-0.02H00 



. 00650 
0.00390 
0.0 

-0 . 00575 
-0.01300 
-0.02320 
-0.03200 



0.00900 
. 00540 
0.0 
-0.00750 
-0.01750 
-0.02910 
-0 . 03820 



0.01200 
6.00730 
0.0 

-0 . 00950 
-0 . 02200 
-0 . 03390 
-0.04320 



0.01500 
0.00780 
0.0 
-0.01100 
-0 . 02450 
-0.03700 
-0.0^730 



0.01780 
. 00930 
0.0 
-0.01200 
-0.02650 
-0 . 03960 
-0.05140 



0.02100 
0.01070 
0.0 
-0.01 300 
-0.029CC 
-0.04200 
-0.05500 



ENGINEER NASA 
DATE """" 



FIGURE 4.1.1.3-69 

EFFECT OF BODY FLAP 



4.1.1.3-75 



Vx 



'1* 



Rockwell International 

Space Division 



VBAR = 0.060 

•p+i i i i i I r i i i m t i i 



DELBF CDEGD 

-25 25 

| I I I I | I I I i | 



U 
Q 



.02 



.0 



.02 



.OH 



-.06 



15 



*-*:- 



I I 1 I 



MIL 



i i i r 




i i i r 



— s 



I i i i 



i i 



J_L 



I I I I 



20 



25 



30 35 t0 

ALPHA CDEG) 



45 



50 



55 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BODY LENGTH LB * 1290.3 


IN. 









ALPHA (DEG) 








20.000 


25.000 


30.000 


35.000 


40 . 000 


45.000 


50 . 000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 






BCOY FLAP PITCHING MOM 


ENT'COEFFI 






-U.700 


0.00400 


. 00650 


. 00900 


0.01200 


0.01500 


0.01780 


0.02100 


' -5.000 


0.002SO 


0.00390 


0.00540 


0.00730 


0.00780 


0.00930 


0.01070 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0.00290 


-0.00550 


-0 . 00700 


-0.00900 


-0.01000 


-0.01100 


-0.01250 


10.000 


-0.00750 


-0.01200 


-0.01500 


-0.01800 


-0.02000 


-0.02150 


-0.02300 


16.300 


-0.01340 


-0.0203O 


-0.02460 


-0.02780 


-0.03000 


-0.03180 


-0.03350 


22.500 


-0.02000 


-0 . 02620 


-0.03180 


-0.03600 


-0.03950 


-0 . 04270 


-0.04460 



ENGINEER NASA 
DATE ™~__! 



FIGURE 4.1.1.3-70 

EFFECT OF. BODY FLAP 



4.1.1.3-76 



SC 72 -£!, CCtC JM 



€> 



Rockwell International 

Space Division 



VBAR 



0.080 



DELBF CDEG) 

-25 25 



U. 

a 




ALPHA CDEG3 



BASELINE 0R81TER VEHICLE 
CENTER OF GRAVITY XO « PS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MOMENT REFERENCE 20 = WL 375.0 IN. 



ATION 




REFERENCE DIMENSIONS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW » 78.056 


FT. 


M.A.C. CW » 39.560 


FT. 


800Y LENGTH LB - 1290.3 


IN. 



DELBF tOSQ) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



20 . 000 
A 



25.000 
8 



30.000 
C 



ALPH A (PEG ) 
35.000 
D 



40.000 
E 



0.00400 
0.00290 
0.0 
-0.00200 
-0 . 00570 
-0.01100 
-0.01670 



0.00650 
. 00390 
0.0 
-0 . 00380 
-0.01000 
-CO 1660 
-0 . 02220 



80DY FLAP PITCHING MOMENT COEFF 



45.000 

F 



50.000 

G 



0.00900 
. 00540 
0.0 
-0.00550 
-0.01250 
-0.02000 
-0.02600 



0.01200 


0.01500 


0.01780 


0.02100 


,0 . 00730 


. 00780 


. 00930 


0.01070 


0.0 


0.0 


0.0 


0.0 


-0.00700 


-0 . 00850 


-0.01000 


-0.01100 


-0.01430 


-0.01580 


-0.01700 


-0.01800 


-0.02190 


-0.02330 


-0.02400 


-0.02500 


-0 . 02830 


-0 . 03000 


-0.03150 


-0.0330C 



ENGINEER NASA 
OATE 



FIGURE 4.1.1.3-71 
EFFECT OF BODY FLAP 



4.1.1.3-77 



SD72~SH-CCeC IM 



* 



Rockwell International 

Space Division 



DELBF CDEG) 

-35 25 

| I I I I | I I I ! | 
■° V i ; I i I I i i < I i i I I I i ! I i I i I i I I i i I I I 1 i i I I i I i I 



ALTITUDE CFT. J = 300000.0 to 600,000 



.08 



CO 

z: 
o 
o 



.02 



--0H 



I I I I 



I I I I 



I I ! I 



I I I I 




,-r-6 



I I I 1 



15 



SO 



25 



30 35 

ALPHA CDEGD 



HO 



45 



50 



55 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE 011-ENSIONS 




CENTER OF GRAVITY X0 • FS 1076.7 IN. 


WING AREA SW • 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 6W » 78.056 


FT. 


MOMENT REFERENCE 20 » WL 375.0 IN. 


M.A.C. CU - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 





ALPHA (DEG) 


20.0 


25.0 


30.0 


35.0 


40.0 


45.0 


50.0 


DELBF (DEG) 


A 


B 


c 


D 


E 


F 


G 






BODY FLAP PITCHING MOM 


ENT COEFFI 






-11.700 


0.00400 


0.00650 


0.00900 


0.01200 


0.01500 


0.01780 


0.02100 


-5.000 


0.00290 


0.00390 


0.00540 


0.00730 


0.00780 


0.00930 


0.01070 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


-0 . 00200 


-0.00380 


-0.00550 


-0.00700 


-0.00850 


-0.01000 


-0.01100 


10.000 


-0.00570 


-0.01000 


-0.01250 


-0.01430 


-0.01580 


-0.01700 


-0.01800 


16.300 


-0.01100 


-0.01660 


-0.02000 


-0.02190 


-0.02330 


-0.02400 


-0 . 02500 


22.500 


-0.01670 


-0. 02220 


-0 . 02600 


-0.02830 


-0.03000 


-0.03150 


-0 . 03300 



ENGINEER 
DATE I 



FIGURE 4.1.1.3-72 

EFFECT OF BODY FLAP 



4.1.1.3-78 



-*" r 



C72- GK-CC6C 1M 



'1* 



Rockwell International 

Space Division 



HACH NUMBER 



0.250 



DELSB CDEGD 

50 100 



111! 



^M 



r 



.08 



.06 



.02 
-10 



1 I I 



I I 1 1 



_LJ_ 



TTTT 



l I I I 



I i I I 




I I I I 



I I i 1 



_L_L 



Ml! 



J_J_ 



TTT 



J I I 



I I I I 



l l I 



I 'I I I 



10 

ALPHA 



15 

CDEGD 



20 



30 



35 



COLORATION 


BASELINE 0R6ITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW » 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MCtENT REFERENCE ZO » WL 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BOOY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0ELS8 (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MOMENT 


I NCR 






0.0 


-0.00970 


-0 . 00970 


-0 . 00970 


-0.00970 


-0 . 00970 


-0.00970 


-0.00970 


-0.00970 


15.000 


-0.00500 


-0 . 00500 


-0 . 00500 


-0.00500 


-0 . 00500 


-0 . 00500 


-0.00500 


-0.00500 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00650 


0.00636 


. 00600 


. 00530 


0.00460 


0.00440 


0.00420 


0.00400 


45.000 


0.01450 


0.01409 


0.01330 


0.01195 


0.01060 


0.00988 


0.00950 


0.00940 


55.000 


0.02330 


0.02227 


0.02110 


0.01970 


0.01830 


0.01704 


0.01500 


0.01660 


70.000 


0.03510 


0.03332 


0.03200 


0.03135 


0.03070 


0.02965 


0.02860 


0.02960 


87.200 


0.04460 


0.04410 


. 04350 


. 04275 


o . 04aoo 


0.04178 


0.04180 


0.04200 



£ngineer33£D 

OATE_5riX-3j£I 



FIGURE 4.1.1.3-73 

EFFECT OF SPEEOBRAKE 



4.1.1.3-79 



€* 



Rockwell International 
Spaca Division 



MACH NUMBER 



0.400 



DELSB CDEG) 

50 100 

I I II I I I I ! 




-.02 



CONFIGURATION 



BASELIMI 0R8ITER VEHICLE 
CENTER 0T GRAVITY XO - FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

MOTCNT REFERENCE ZO • U. 375.0 IN. 



REFERENCE OlfENSIONS 
WING AREA SW - 3690.00 SQ.FT. 
WING SPAN BW - 79.055 FT. 
M.A.C. CW - 39.560 FT. 

BOOV LENGTH LB ■ 1550.3 IN. 



1 








ALPHA 


tOEG) 










-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELSB JOEG) 


A 


B 


c 





E 


F 


G 


H 






SPEED 


BRAKE PITCHING MOMENT 


INCR 






0.0 


-0.00970 


-0.00970 


-0.00970 


-0.00970 


-0.00970 


-0.00970 


-0.00970 


-0.00970 


15.000 


-0.00500 


-0.00500 


-0.00500 


-0.00500 


-0.00500 


-0.00500 


-0.00500 


-0.00500 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00650 


0.00636 


0.00600 


0.00530 


0.00*60 


0.00**0 


0.00*20 


. 00*00 


*5.000 


0. 01*50 


0.01*09 


0.01330 


0.01195 


0.01060 


0.00988 


0.00950 


0.009*0 


55.000 


0.02330 


0.02227 


0.02110 


0.01970 


0.01830 


0.0170* 


0.01600 


0.01660 


70.000 


0.03510 


0.03332 


0.03200 


0.03135 


0.03070 


0.02965 


0.02860 


0.02860 


87.200 


0.04*60 


o. emtio 


0. OH 350 


0.0*275 


0.0*200 


0.0*178 


0.0*180 


0.0*200 



ENGINEER J^(it> 
OXTZ.SL-Jj.z3z~ 



FIGURE 4.1.1.3-74 

FFFFHT OF SPEEDBRAKE 



4.1.1.3-SO 



i L V : 



._ . .. ^ . hi 



* 



Rockwell International 

Space Division 



HACH NUMBER 



. 10r 



.08 



.06 



CD 
Q 



..oaLi-i 



I I I 



0.S00 

lir 



DELSB CDEG) 

50 100 

| I l I i | I I I I | 



J_L 



I I I I 



I I I 




I I I 



I I 



I l I 



I l ' I I 



_L_L 



III! 



I 1 1. 



-10 



10 
ALPHA 



15 

CDEGD 



20 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO = FS 107S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


CR YO • 8L 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MCf-CNT REFERENCE 20 » WL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB = 1390.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEG) 


A 


B 


C 





E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MGtCNT 


INCR 






0.0 


-0.00686 


-0.00746 


-0.00806 


-0 . 00686 


-0 . 00657 


-0 . 00597 


-0.00537 


-0.00477 


15.000 


-0.00397 


-0 . 00400 


-0.00403 


-0.00400 


-0.00300 


-0.00270 


-0.00240 


-0.00210 


55.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00942 


. 00877 


0.00811 


0.00828 


. 00883 


0.00881 


0.00879 


. CC878 


45.000 


0.01873 


0.01743 


0.01814 


0.01652 


0.01740 


0.01734 


0.01729 


0.01723 


55.000 


0.02776 


0.02589 


0.02402 


. 02465 


0.02547 


0.02535 


0.02523 


0.02511 


70.000 


0.03750 


0.03499 


0.03529 


. 03500 


0.03500 


0.03500 


0.03500 


0.03500 


87.200 


. 04470 


. 04485 


. 04500 


. 04500 


0.04433 


0.04300 


0.04167 


0.04034 



ENGINEER £ 
OATE.fkCS-? 



FIGURE 4.1.1.3-75 

EFFECT OF SPEEDBRAKE 



4.1.1.3-31 



\ v — n 
* L i — - 



ccec Kvi 



e 



Rockwell International 

Space Division 



MACH NUMBER 



.08 



CO 

o 

o 



-.02 



" ! I 'T 



..1...I I 1 



III! 



JLJ-.L 



i I I I 



0.800 

I I I i 



DELSB CDEGD 

50 100 

| I I I I | I I II | 



_L_L 



'?■ — * 




I I I I 



i i"l"'l" 



I i i T~ 



.1..I L ! 



I I I l 



1 I IT 



I I L 



I I I I 



I I I I 



I I I I 



I I ' I 



■10 



to 

ALPHA 



15 
CDEGD 



20 



.25 



30 



35 



CONFIGURATION 




BASELINE OR3ITER VEHICLE 


REFERENCE DirENSIONS 




CENTER OF GRAVITY XO ■ FS 1076.7 IN. 


WING AREA SW • 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCfCNT REFERENCE ZO =• WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB - 1290.3" 


IN. 



, 








ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELSB (C€G) 


A 


B 


C 





E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MCfrENT INCH 






0.0 


-0.00612 


-0.00653 


-0.00694 


-0 . 00675 


-0.00770 


-0 . 00688 


-0.00606 


-0.00524 


15.000 


-0.00355 


-0.00340 


-0.00325 


-0.00313 


-0.004 06 


-0.00423 


-0.00440 


-0 . 00457 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00900 


0.00898 


0.00896 


0.00871 


0.00741 


0.00768 


0.00794 


0.00821 


45.000 


0.01810 


0.01789 


0.01758 


0.01715 


0.01568 


0.01572 


0.01576 


0.01579 


55.000 


0.02739 


0.02668 


0.02597 


0.C2521 


0.02431 


0.02392 


0.02353 


0.02314 


70.000 


0.04167 


0.03924 


0.03681 


0.03653 


0.03619 


0.03500 


0.03381 


0.03262 


87.200 


0.05818 


0.05473 


0.05123 


0.04904 


0.04639 


0.04500 


0.04361 


. 04222 



ENGINEER ^ 
OATE„a.-li-rTieL 



FIGURE 4.1.1.3-76 

EFFECT OF SPEEDBRAKE 



4.1.1.3-S2 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 



0.900 



DELSB CDEGD 

O 50 100 

i t i r 



x. 

Q 




CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO = FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO = H. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 3690.00 SQ.FT. 
WING SPAN BW - 7S.C56 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB =■ 1590.3 IN. 



DELSB (PEG) 



0.0 

15.000 

as. ooo 

35.000 
45.000 
55.000 
70.000 
87.500 



10.000 
A 



-5.000 
B 



0.0 

C 



ALPHA (OEG) 



5.000 




10.000 

E 



15.000 

F 



-0.00576 
-0.00390 

0.0 

0.01049 

o.oaoea 

0.02919 
0.04576 
0.06399 



-0.00597 
-0.00460 
0.0 

0.00838 
0.01822 
0.02858 
0. 04383 
0.06219 



SPEEOeRAKE PITCHING MOMENT [NCR 



20.000 
G 



25.000 
H 



-0.00618 
-0.00570 
0.0 

0.00626 
0.01577 
0.02797 
0.04190 
. 06039 



-0.00811 
-0.00571 
0.0 

0.00737 
0.01647 
0.02641 
0.04000 
. OS600 



-0.00930 
-0.00650 
0.0 

0.00601 
. 1 349 
0.02299 
0.03800 
. 05500 



-0.00649 
-0.00341 
0.0 

0.00646 
0.01373 
0.02176 
0.03699 
0.05186 



-0.00368 
-0.00300 
0.0 

0.00691 
0.01397 
0.02053 
0.03598 
. 04872 



-0.00087 
-0.00200 
0.0 

0.00736 
0.01422 
0.01930 
0.03497 
0.04558 



ENGINEER 



FIGURE 4.1.1.3-77 

EFFECT OF SPEEDBRAKF 



4.1.1.3-33 



£ I 7 £ - S h - C t I C I VI 



* 



Rockwell International 

Space Division 



MACH NUMBER 
10 . i . , i 



0.950 



DELSB CDEG) 

50 100 



CD 



U 

Q 




10 15 

ALPHA CDEGD 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE OlhENSIONS 




CENTER Cf GRAVITY XO - F5 107E.7 IN. 


WING AREA SW = 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW =■ 78.055 


FT. 


MOMENT REFERENCE ZO « UL 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BODY LENGTH L8 - 1 290. J 


IN. 











ALPHA 


(DEG; 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELSB CDEG> 


A 


S 


C 





E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MCtCNT 


INCR 






0.0 


-0.00450 


-0.00500 


-0.00550 


-0.00600 


-0.00650 


-0.00700 


-0.00750 


-0 . 00800 


ts.ooo 


-0.00300 


-0.00300 


-0.00300 


-0.00350 


-0.00434 


-0.00400 


-0.00366 


-0.00332 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.01065 


0.00941 


0.00816 


0.00715 


0.00737 


0.00698 


0.00660 


0.00622 


45.000 


0.01940 


0.01795 


0.01650 


0.01514 


0.01469 


0.01419 


0.01370 


0.01320 


55.000 


0.02S32 


0.02566 


0.02500 


0.02375 


0.02198 


0.02159 


0.02120 


0.02081 


70.000 


0.04494 


0.04297 


0.04100 


0.03756 


0.03569 


0.03335 


0.03101 


. 02867 


87.200 


0.06730 


. 06465 


0.06200 


. 05700 


0.05197 


0.04836 


0.04475 


0.04! 14 



ENGINEER 
DATE 



EER_C£j> 



FIGURE 4.1.1.3-78 

EFFECT OF SPEEDBRAKE 



4.1.1.3-^4 



sr 12-sii- ck Co i,\i 



41 



Rockwell International 

Space Division 



MACH NUMBER 



0.980 



OELSB CDEG3 

50 100 



CD 

en 

Q 




10 15 

ALPHA CDEGD 



CONFIGURATION 



BASELINE CR8ITER VEHICLE 
CENTER CF GRAVITY XO =■ FS 1078.7 IN. 
OR YO = BL 0.0 IN. 

MOENT REFERENCE ZO « WL 375.0 IN. 



REFERENCE DlhENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW => 39.560 FT. 

BODY LENGTH LB - 1590.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


CELSB (DEG) 


A 


8 


C 





E 


F 


G 


H 






SPEED 


eRAKE PITCH 


ING MOt-ENT 


I NCR 






0.0 


-0.00386 


-0.00439 


-0.00481 


-0 . 00485 


-0.00494 


-0 . 00646 


-0.00741 


-0.00803 


15.000 


-0.00301 


-0.00283 


-0.00280 


-0 . 00334 


-0.00347 


-0.00388 


-0.00359 


-0 . 00366 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.01103 


0.00993 


0.00866 


0.00734 


0.00754 


0.00719 


0.00659 


0.00607 


45.000 


0.02040 


0.01904 


0.01711 


0.01521 


0.01503 


0.01440 


0.01370 


0.01303 


55.000 


0.02807 


0.02741 


0.02463 


0.02309 


0.02169 


0.02158 


0.02141 


0.02132 


70.000 


0.04676 


0.04359 


0.04103 


. 03720 


. 03493 


0.03271 


0.03071 


. 02787 


87.200 


0.06918 


0.06582 


0.06246 


. 05725 


0.05094 


0.04813 


0.04392 


0.C4009 



ENGINEER t&X? 

oate„3t3XE:3El 



FIGURE 4.1.1.3-79 

EFFECT OF SPEEDBRAKE 



4.1.1.3-35 



[ ', : 



C i iVl 



a 



Rockwell Internntiun.-il 



CDLGJ 



NACH NUMBER 



1.050 



a 

CO 

cj 

a 




COFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OT GRAVITY XO - FS 1076.7 IN. 

OR YO « BL 0.0 IN. 

MCftNT REFERENCE ZO » WL 375.0 IN. 



REFERENCE OIf-£NSlCNS 
WING AREA SW * 2690.00 SQ.FT. 
WING SPAN 9W - 79.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB - 1390.3 IN. 











ALPHA 


ICEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELS8 tDEG) 


A 


B. 


C 


O 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MOCNT 


I NCR 






0.0 


-0.00271 


-0.00265 


-0 . 00225 


-0.00247 


-0.00154 


-0.00319 


-0 . 00458 


-0.00428 


15.000 


-0. 00+23 


-0.00372 


-0.00317 


-0.00317 


-0.00250 


-0.00299 


-0.00324 


-0.00362 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.01232 


0.01096 


0.00952 


0.00856 


0.00738 


0.00740 


. 00708 


. 00707 


45.000 


0.02550 


0.02241 


0.01903 


0.01677 


o.otsoo 


0.01471 


0.01423 


0.01386 


55. CC0 


0.03S91 


0.03252 


. 02742 


0.02427 


0.02197 


0.02181 


0.02151 


0.02137 


70.0CO 


0.05359 


0.0V794 


0.04278 


0.03662 


0.03H94 


. 03339 


0.03193 


0.03005 


97. =00 


0.07319 


. 06753 


0.06190 


0.05672 


0.05068 


0.04822 


. 04497 


0.04158 



L-GINEER Dfi£L 

:ate...2?IE-!I!E 



FIGURE 4.1.1.3-80 

FFFFCT OF SPEEOBRAKE 



U. 1.1. 3-86 



v. L. 



I - 



:,-Cl> C 



:Vl 



'Jt 



Rockwell International 

Space Division 



GO 
(-0 

a 



MACH NUMBER 



1. 100 



DELS8 CDEG) 

50 100 




CONFIGURATION 



BASELINE CR8ITER VEHICLE 

CENTER Cf GRAVITY XO » FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MO-tNT REFERENCE 20 - W_ 375.0 IN. 



REFERENCE OII^ENSIONS 
WING AREA SW » 2690.00 SQ.FT. 
WING SPAN SW = 78.055 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LS = 1290.3 IN. 



DELS8 (DEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



-10.000 
A 



-5.000 
B 



0.0 

c 



ALPHA (0EG) 



5.000 
O 



10.000 
E 



15.000 

F 



20 . 000 
G 



25.000 
H 



-0.00256 
-0 . 00453 
0.0 

0.01307 
0.02798 
0.0H132 
0.05882 
0.07630 



-0.00184 
-0.00384 
0.0 

0.01165 
0.02453 
0.03637 
0.05253 
. 06940 



5PEED6RAKE PITCHING MOTCNT INCR 



-0.00102 
-0.00315 
0.0 

0.01024 
0.C2107 
0.03142 
0.04624 
0.0E250 



-0.00168 


-0.00019 


-0.00187 


-0 . 00355 


-0.00300 


-0.00298 


-0.00221 


-0.00259 


-0.00298 


-0.00337 


0.0 


0.0 


0.0 


0.0 


0.0 


0.00903 


0.00720 


0.00716 


0.00712 


0.00708 


0.01819 


0.01538 


0.01484 


0.01430 


0.01376 


0.02735 


0.02366 


0.02255 


0.02144 


0.02033 


0.04112 


0.03642 


. 03427 


0.03213 


0.02999 


0.05700 


0.05180 


. 04808 


0.04436 


0.04064 



engineer u&d 
date„VT2E:t3: 



FIGURE 4.1.1.3-31 

EFFECT OF SPEEDBRAKE 



4.1.1.3-87 



£ i 72-sn-cceo im 



w 



Rockwell International 

Space Division 



00 
(ft 

U 

a 



MACH NUMBER 



1.200 



DELSB CDEG) 

50 100 

| I I I I | I I I I 




15 

CDEGD 



BASELINE CRBITER VEHICLE 

CENTER OF GRAVITY XO • FS 1076.7 IN. 

OR YO • BL 0.0 IN. 

MOttNT REFERENCE ZO - WL 375.0 IN. 



ATION 




REFERENCE DIt-tNSIONS 




WING AREA SW » 2690.00 


SQ.FT. 


WING SPAN BW - 78.056 


FT. 


M.A.C. CW » 39.560 


FT. 


BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


tDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELS3 (DEG) 


A 


8 


C 


D 


E- 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MCf£NT 


INCR 






0.0 


-0 . 00600 


-0.00560 


-0.00520 


-0.00501 


-0.00480 


-0.00450 


-0.00420 


-0 . 00390 


15.000 


-0.00250 


-0.00250 


-0.00250 


-0.00250 


-0.00250 


-0.00246 


-0.00242 


-0.00238 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.01404 


0.01297 


0.01191 


0.00791 


0.00666 


0.00552 


0.00439 


0.00325 


45.000 


. 02908 


0.02911 


0.02713 


0.02175 


0.01799 


0.01490 


0.01181 


. 00872 


55.000 


0.04435 


0.04413 


0.04391 


0.03904 


0.03200 


0.02650 


0.02100 


0.01550 


70.000 


0.07026 


0.06500 


0.05974 


. 04944 


0.04300 


0.03700 


0.03100 


. 02500 


87.200 


0.08829 


0.08113 


0.07397 


0.06344 


0.05700 


0.04739 


0.03778 


0.02817 



ENGINEER 
OATE„!X-J. 



E3EI 



FIGURE 4.1.1.3-32 

EFFECT OF SPEEDBRAKE 



4.1.1.3-88 



x_> 



£ D ' 2 - s i ■■■; - c c ( c i .vi 



* 



Rockwell International 

Space Division 



MACH NUMBER 
■«o-f i ■ ' 



.06 



CD 
CO 

u 

Q 



-.oa 



1.300 
r~i i i i i i i i I i i 



i i i i 



-L-l. I 1 



1 I I I 



i i ii — m 




111! 



I I I I 



DELSB CDEG) 

50 100 



J .1 1 I 



I I I..-L 



I I I I 



.L.L..1 I 



-10 



10 

ALPHA 



15 
CDEGD 



20 



25 



i I If 



I I i I 
30 35 



CONFIGURATION 




BA5ELINE ORBITER VEHICLE 


REFERENCE OIMENSIOS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO = BL 0.0 IN, 


WING SPAN BW - 78.056 


FT. 


MOENT REFERENCE 20 - UL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB » 1290.7 


in:' 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0ELS8 (CEG) 


A 


B 


C 





E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING M0TENT 


INCR 






0.0 


-0.00575 


-0.00549 


-0 . 00525 


-0 . 00532 


-0.00477 


-0.00404 


-0 . 00332 


-0 . 00250 


15.000 


-0.00353 


-0.00315 


-0.00276 


-0 . 00308 


-0.00294 


-0.00221 


-0.00159 


-0.00097 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00922 


0.00960 


0.00998 


. 00704 


0.00640 


0.00579 


0.00519 


0.00458 


45.000 


0.02351 


0.02281 


0.02210 


0.01824 


0.01585 


0.01425 


0.01266 


0.01106 


55.000 


0.04002 


0.03774 


0.03545 


0.03186 


0.02723 


0.02435 


0.02147 


0.01858 


70.000 


0.06313 


0.05812 


0.05312 


0.04546 


0.04033 


0.03694 


0.03303 


0.02938 


87.200 


0.08174 


0.07499 


. 08323 


. 05905 


0.05 163 


0. 0^486 


0.03809 


0.03132 



ENGINEER J^J^ 



FIGURE 4.1.1.3-83 

EFFECT OF SPEEDBRAKE 



4.1.1.3-89 



SE 



7 2 - S h 



cect im 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.500 



CD 
CO 

2: 
<_> 
o 



.to 



.08 



.06 



.04 



.02 



DELSB CDEG3 

50 100 

r~i n~\ r~i r~r~ ] 



•°.=z=: 



.oa 1 - 
-10 



1 1 i 



llli 



1 1 I 



I i I 



i ! I I 



I I I I 



i I I I 




lil! 



1 I 1 I i I I 1 



ts^*=ir 



1 1 



iii' 



' 1 1 



1 1 1 1 



-5 



10 

ALPHA 



15 

CDEG3 



20 



25 



30 



35 



CONFIGURATION 




BASELIf-E 0R8ITER VEHICLE 


REFERENCE OlrCNSIONS 




CENTER Cf GRAVITY XO = FS 1076.7 IN. 


WING AREA SW - 2590.00 


SQ.FT. 


OR Y0 - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MGtCNT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB - 1290.7 


IN. 











ALPHA 


COEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (C€G) 


A 


B 


C 


□ 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MCftNT 


INCR 






0.0 


-0.00544 


-0.00534 


-0.00529 


-0 . 00552 


-0.00466 


-0.00348 


-0.00232 


-0.00118 


15.000 


-0.00469 


-0.00404 


-0.00323 


-0.00377 


-0.00324 


-0.00197 


-0.00074 


0.00047 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00397 


0.00587 


0.00747 


0.00617 


0.00590 


0.00592 


0.00590 


0.00585 


45.000 


0.01739 


0.01691 


0.01596 


0.01425 


0.01292 


0.01297 


0.01314 


0.01318 


55.000 


0.03265 


0.02966 


0.02545 


0.02356 


0.02115 


0.02072 


0.02113 


0.02118 


70.000 


0.05258 


0.04828 


0.04389 


0.03946 


0.03566 


0.03526 


0.03425 


0.03324 


87.200 


0.07139 


0.05609 


0.06095 


0.05318 


. 04496 


0.04160 


0.03855 


0.03422 



ENGIfCER J&& 

DATE„iL-j:fe-:-5:: 



FIGURE 4.1.1.3-84 

EFFECT OF SPEEDBRAKE 



4.1.1.3-90 



szs 



- 1. / 



'i* 



Rockwell International 
Space Division 



MACH NUMBER 

!j | i I 1 i I l 



2.000 



DELSB CDEGD 

50 100 




10 15 20 

ALPHA CDEGD 



CONFIGURATION 



BASELINE CR3ITER VEHICLE 
CENTER OF GRAVITY XO =» FS 1076.7 IN. 
OR YO - 8L 0.0 IN. 

MOMENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DlhENSIONS 
WING AREA SW ' 2690.00 SQ.FT. 
WING SPAN 8W ' 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB » 1390. 3 IN. 



CCLS3 (DEG) 



0.0 
15.000 
85.000 
35.000 
45.000 
55.000 
70.000 
87.200 



-10.000 
A 



-5.000 
B 



0.0 
C 



ALPHA (PEG) 



5.000 




10.000 

E 



15.000 

F 



-0.00562 
-0 . 00423 
0.0 

. 00727 
0.01536 
0.024 34 
0.04223 
0.06057 



-0.00537 
-0.00395 
0.0 

0.00668 
0.01429 
0.02282 
0.03919 
0,05727 



-0.00512 
-0.00358 
0.0 

0.00609 
0.01322 
0.02130 
0.03615 
0.05397 



SPEEOeRAKE PITCHING MOMENT I NCR 



20 . 000 
G 



25.000 
H 



30.000 
I 



-0.00487 
-0.00340 
0.0 

0.00551 
0.01215 
0.01978 
0.03311 
0.05067 



-0.00414 
-0.00292 
0.0 

0.00474 
0.01063 
0.01747 
0.02917 
. 04548 



-0.00406 
-0.00276 
0.0 

0.00438 
0.00984 
0.01622 
0.02718 
0.04294 



-0.00377 
-0.00241 
0.0 

0.00375 
0.00811 
0.01307 
0.02334 
0.03750 



-0.00348 
-0.00207 
0.0 

0.00313 
0.00637 
0.00992 
0.01950 
0.03206 



-0.00319 
-0.C0172 
0.0 

0.00250 
0.00464 
. 00677 
0.01566 
0.02662 



ENGINEER £&b 
0AT£_gb.iS=g5L"" 



FIGURE 4.1.1.3-85 

EFFECT OF SPEEDBRAKE 



4.1.1.3-91 



St72-SH~CCec 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



3.000 



.10 



.08 



.05 



DELSB CDEGD 

50 1 00 

| l I I l | I I i , | 



CD 

en 

31 

a 

a 



-.02 



Tl'i I 



1 1 1 



I i i i 



III! 



IT 



I I I 



Mil 



I I I I 



I I I 




III! 



I I I I 



I 1 I 



I I I 



I I 1 



-10 



10 

ALPHA 



15 

CDEG) 



20 



25 



30 



CCfF I GURATION 


BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO » FS 1076.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - a. 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE ZO = WL 375.0 IN. 


M.A.C. CW = 39.560 FT. 




BODY LENGTH LB = 1290.3 IN. 











ALPHA 


<C€G) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (DEG) 


A 


8 


C 





E 


F 


G 


H 






SPEED 


BRAKE PITCH 


1NG MOMENT 


I NCR 






0.0 


-0.01075 


-0.01023 


-0.00972 


-0.00920 


-0.00795 


-0.00735 


-0.00540 


-0 . 00383 


15.000 


-0.00430 


-0.00409 


-0.00389 


-0 . 00368 


-0.00318 


-0.00294 


-0.00216 


-0.00153 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00391 


0.00376 


0.00351 


. 00346 


0.00293 


0.00270 


0.00182 


0.00121 


45.000 


0.00953 


0.00895 


0.00837 


0.00780 


0.00689 


0.00637 


0.00510 


0.00377 


55. COO 


0.01545 


0.01532 


0.01419 


0.01306 


0.01183 


0.01095 


0.00950 


0.00750 


70.000 


0.02683 


0.02556 


0.02429 


. 02302 


0.02067 


0.01916 


0.01700 


0.01450 


87.200 


0.04333 


0.04107 


0.03881 


0.03655 


0.03325 


0.03111 


0.02750 


0.02400 



ENGINEER S&£) 
OATE_j_S::-?rl7,iS 



FIGURE 4.1.1.3-86 

EFFECT OF SPEEDBRAKE 



4.1.1.3-92 



t ; 



--oH-CCtC iM 



€> 



Rockwell International 

Space Division 



r 



MACH NUMBER 



3.000 



DELSB CDEGD 
q 50 100 

pi I i i | i i i i - ] 



CD 
X. 

a 



-.02 




20 



25 



30 35 40 

ALPHA CDEG3 



45 



50 



CONFIGURATION 


BASELINE CRBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW =■ 2S90.00 SQ.FT. 


OR YO » 8L 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MOMENT REFERENCE 20 - ML 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BCOY LENGTH LB - 1290.3 IN. 





ALPHA (CEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELSB (DEG) 


F 


G 


H 


I 


J 


K 


L 






SPEEDBRAKE 


PITCHING MO 


fENT INCR 






0.0 


-0.00735 


-0.00540 


-0.00383 


-0.00227 


-0.00100 


-0.00087 


-0.00050 


15.000 


-0.00294 


-0.00216 


-0.00153 


-0.00091 


-0.00050 


-0.00035 


-0.00030 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00270 


0.00182 


0.00121 


0.00060 


0.00050 


0.00050 


0.00154 


45.000 


0.00637 


0.00510 


0.00377 


0.00243 


0.00154 


0.00100 


0.00200 


55.000 


0.01095 


0.00950 


0.00750 


0.00550 


0.00485 


0.00400 


0.00400 


70.000 


0.01916 


0.01700 


0.01450 


0.01200 


0.00900 


0.00800 


0.00700 


87.200 


0.03111 


0.02750 


0.02400 


0.02050 


0.01700 


0.01350 


0.01000 



ENGINEER ^*^_ 
OATE_LO£3r?!£_ 



FIGURE 4.1.1.3-87 

EFFECT OF SPEEDBRAKE 



55 



4.1.1.3-93 



£E ^-oH-OCeO 1M 



€> 



Rockwell International 

Space Division 



MACH NUMBER 



4.000 



.10 



.08 



.06 



DELSB CDEGD 

50 

1 I • I U ' 



100 



CO 

■z. 
o 
o 



.02 



Mil 



1 11 



till 



TT 




J-JL 



I I I I 



I I I I 



I I I I 



I I I I 



s-is . j ^C, Li u n g~gr^rt> »a ~s-^i> ^ t- r^ 



i i i i 



i i I I 




i i i : | 
i i i i 



iiti 



i i i i 



I.1...L1. 



-10 



10 

ALPHA 



15 

CDEGD 



20 



30 



35 



w 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW * 2690.00 


SQ.FT. 


OR YO > BL 0.0 IN. 


UING SPAN 6W - 78.056 


FT. 


MOCNT REFERENCE ZO « UL 375.0 IN. 


M.A.C. CW = 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELSB (DEG) 


A 


8 


C 





E 


F 


G 


H 






SPEED 


6RAKE PITCH 


ING MOMENT 


INCR 






0.0 


-0.00318 


-0.00218 


-0.00158 


-0.00158 


-0.00158 


-0.00124 


-0.00079 


-0.00058 


15.000 


-0.00133 


-0.00089 


-0.00063 


-0.00063 


-0.00063 


-0.00050 


-0.00032 


-0.00023 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00403 


0.00366 


0.00329 


0.00293 


0.00256 


0.00214 


0.00162 


0.00107 


45.000 


0.008O6 


0.00732 


0.00658 


0.00586 


0.00512 


0.00428 


0.00324 


0.00214 


55.000 


0.01208 


0.01098 


0.00988 


0.00878 


0.00768 


0.00641 


0.00486 


0.00320 


70.000 


0.02423 


0.02198 


0.01983 


0.01776 


0.01583 


0.01345 


0.00965 


0.00593 


87.200 


0.03897 


0.03537 


0.03187 


0.02943 


0.02517 


0.02152 


0.01515 


. 00906 



ENGINEER 
0ATE___6&1 



& 



FIGURE 4.1.1.3-88 

EFFECT OF SPEEDBRAKE 



4.1.1.3-94 



CiCLC 1M 



'I* 



Rockwell International 

Space Division 



MACH NUMBER 



■lOr 



T~r 



Q 



.08 



.06 



.C4 



.02 



.0 ,» 



-.02 



TT 



I I I 1 



4.000 

ill! 



DELSB CDEGD 

50 100 

I I I I I I I I I 




TTTT 



I I I i I I I i I 



■j ^ S fffif f fi^ ^^g 



15 



SO 



1 I I I l l l I I i I I 



I V i" 



Wfrfc-tfrb 



30 35 40 

ALPHA CDEGD 



*45 



r 



CCtflGURATION 




baseline orsiter vehicle 


REFERENCE DIMENSIONS 




CENTER 0T GRAVITY X0 - FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


CR YO * BL 0.0 IN. 


WING SPAN BW = 78.056 


FT. 


MC*ENT REFERENCE 20 » WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB ■ I2S0.3 


IN. 



ENGINEER Xc»X> 
0ATE__AJg£3gI 



FIGURE 4.1.1.3-89 

EFFECT OF SPEEDBRAKE 



I l I I 



t — t- 



i l i 



50 







ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


0ELS8 (DEG) 


F 


G 


H 


I 


J 


K 


L 






SPEEDGRAKE 


PITCHING MO 


MENT I NCR 






0.0 


-0.00124 


-0.00079 


-0.00058 


-0.00010 


0.00037 


0.00130 


0.00160 


15.000 


-0.00050 


-0.00032 


-0.00023 


-0 . 0000"+ 


0.00009 


0.00036 


0.00056 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.002m 


0.00162 


0.00107 


0.00074 


0.00049 


0.00014 


0.0 


45.000 


0.00428 


0.00324 


0.00214 


0.00149 


0.00097 


0.00028 


0.0 


55.000 


0.00641 


0-00486 


0.00320 


0.00223 


0.00146 


0.00043 


0.0 


70.000 


0.01345 


0.00965 


0.00593 


0.00373 


0.00210 


0.00033 


0.0 


87.200 


0.02152 


0.01515 


0.00906 


0.00544 


. 00307 


0.00054 


0.0 



4.1.1.3-95 



€* 



Rockwell International 

Space Division 



CO 

en 

u 
o 



MACH NUMBER 



5.000 



DELSB CDEG) 

50 100 

| I I I I | I I I I t 



.08 



.06 



.04 



.02 



.0 



.02 



Ml! 


I , 1 1 


1 i 1 1 


MM 


MM 


MM 


I 1 1 1 


III! 


MM 


_ 














- 


_ 
















— 


- 




~y- 


~y~ 


_ ^_ 








— 


- 


~~~^B 






~-p& — ~~ 


&■ _^ 






^-^: 


III! 


! 1 1 1 


MIL 


ill! 


I I I I 


1 1 1 1 


III! 


! ! 1 1 


1 1 1 l~ 



•10 



10 15 

ALPHA CDE6D 



20 



25 



30 



35 



^m 



CONFIGURATION 






baseline orbiter vehicle 


REFERENCE 


DI^ENSIONS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA 


SW - 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN 


8W » 78.055 


FT. 


M0t€NT REFERENCE ZO - U_ 375.0 IN. 


H.A.C. 


CU - 39.560 


FT. 




BODY LENGTH LB » 1290.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELS8 (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MGt€NT 


INCR 






0.0 


-0.00275 


-0.00299 


-0 . 00275 


-0.00180 


-0.00085 


-0.00088 


-0.00056 


-0.00049 


15.000 


-0.00104 


-0.00113 


-0.00104 


-0.00069 


-0.00034 


-0.00035 


-0.00022 


-0 . 00020 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00284 


0.00268 


0.00248 


0.00222 


0.00194 


0.00158 


0.00102 


0.00061 


45.000 


0.00569 


0.00536 


0.00495 


0.00443 


0.00388 


0.00316 


0.00204 


0.00122 


55.000 


0.00853 


0.00804 


0.00743 


0.00665 


0.00583 


0.00474 


0.00307 


0.00183 


70.000 


0. 01900 


0.01759 


0.01600 


0.01422 


0.01230 


0.00988 


0.00634 


0.00349 


87.200 


0.03142 


0.02853 


0.02562 


0.02257 


0.01972 


0.01577 


0.01009 


0.00539 



ENGINEER i£->"t 

0ATE„5rl2=£'JI 



FIGURE 4-1.1.3-90 
EFFECT OF SPEEDBRAKE 



4.1.1.3-96 



cL 72-Sn-0CC0 JM 



a 



Rockwell International 

Space Division 



T~ 



MACH NUMBER 



5.000 



DELSB CDEGD 

50 100 



o 
a 



.08 



.06 



.C4 



.02 



-.02 



r~i i i i i i i i i r~i r~r~i tt~i mini 



(! — c- 



I I [ I 



■F=S= 



I ! I 1 



-L. I., I.I 




I. I 1 , .L, 



I I I 



I I I I I ! I 



■S ffC^Mti KLU . H M B.H 



I , 1 I,. 



I I I 1 



.1-1 I 1. 



H~ -M M— 



_L_L_I_J_ 



!5 



80 



25 



30 



35 

ALPHA 



HO 

CDEG3 



45 



50 



55 



60 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER Of GRAVITY XO - FS 107S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOtNT REFERENCE ZO =■ WL 375.0 IN. 


M.A.C. CW - '39.560 


FT. 




BCOY LENGTH L8 - 1290.7 


IN. 





AIPHA (DEG) 






15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELS8 (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEED 


BRAKE PITCHING M>€NT 


INCH 






0.0 


-0.00088 


-0.00056 


-0.00049 


-0.00017 


0.0 


o.o 


0.0 


0.0 


15.000 


-0.00035 


-0.00022 


-0.00020 


-0 . 00007 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00158 


0.00102 


0.00061 


0.00043 


0.C0003 


0.0 


0.0 


0.0 


45.000 


0.00316 


0.00204 


0.00122 


0.00086 


0.00006 


0.0 


0.0 


0.0 


55.000 


0.004 74 


0.00307 


0.00183 


0.00130 


0.00010 


0.0 


0.0 


0.0 


70.000 


0.00S88 


0.00634 


0.00349 


0.00247 


0.00082 


0.0 


0.0 


0.0 


87.200 


0.01577 


0.01009 


. 00539 


0.00382 


0.00177 


0.0 


0.0 


0.0 



ENGINEERJ^-^ 
0ATE_3iC3E3El 



FIGURE 4.1.1.3-91 

EFFECT OF SPEEOBRAKE 



4.1.1.3-97 



a 



Rockwell International 

Space Division 



MACH NUMBER 



8.000 



DELSB CDEGD 

50 100 

i i i i | i : i i 



CD 
CO 

z: 
u 

Q 




COTf IGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO » FS 1076.7 IN. 

OR YO « SL 0.0 IN. 

MOENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DirtNSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW » 78. 055 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENGTH LB ■ 1290.3 1 IN. 











ALPHA 


(CEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (CEG) 


A 


B 


C 





E 


F 


G 


H 






SPEEDBRAKE PITCHING MOf^NT 


[NCR 






0.0 


-0.00160 


-0.00180 


-0.00160 


-0.00080 


0.0 


0.0 


0.0 


0.0 


15.000 


-0. 00060 


-0 . 00067 


-0.00060 


-0.00030 


0.0 


0.0 


0.0 


0.0 


35.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


o. 00142 


0.00138 


0.00124 


0.00108 


0.00055 


0.00032 


0.00007 


0.0 


45.000 


0.00355 


0.00340 


0.00320 


0.002BO 


0.00190 


0.00125 


0.00070 


0.00010 


55.000 


0. 00648 


0.00618 


0.00575 


0.00500 


0.00392 


0.00267 


0.00150 


. 00058 


70.000 


0. 01345 


0.01270 


0.01155 


0.00995 


0.00800 


0.00540 


0.00310 


0.00145 


87.200 


0.02770 


0.02550 


0.02210 


0.01810 


0.01370 


0.00915 


0.00530 


0.00270 



ENGINEERl^Lal^ 
QATE„.3£GS3C 



FIGURE 4.1.1.3-92 

FFFFCT OF SPEEDBRAKE 



4.1.1.3-98 



SD 



n 



-c 



C 1 iVl 



'1* 



Rockwell International 

Space Division 



CO 

c 



MACH NUMBER 



8.000 



.10; 



L 1 



TTT 



.08 



.06 



.OH 



.02 



ill! 



DELSB CDEGD 

50 100 

I I I I 



-.Qgl 1111 



.0 r r r f - J^^^ ^ zkrinT^^^ 



J_L 



i i i 



go f fe jis fe 



1 ! I I 



ri r 



15 



20 



J- I I I . 



TT 



i I i i i i 



n^f&^j- JBV-Xu l » h m » . 



25 



TTTT 



W LICL IL? LH. M J 4 -i " i -> 4. 



30 



I I I I 



I I I I 
Mill 



M M ' M ■ ■ 



i i i 



35 

ALPHA 



40 

CDEG3 



45 



50 



55 



CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER Cf GRAVITY XO * FS 107S.7 IN. 

CR YO - BL 0.0 IN. 

MONENT REFERENCE ZO - Ml 375.0 IN. 



REFERENCE DIhENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CW « 39.560 FT. 

800V LENGTH LB ■ 1290.7 IN. 



engineer 2x>d 
oate„3=I3E35l 



FIGURE 4.1.1.3-93 

EFFECT OF SPEEDBRAKE 



60 











ALPHA (OEG) 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


C€LSB (OEG) 


F 


G 


H 


I 


J 


K 


L 


M 




SPEEDBRAKE PITCHING MTK-FNT 


INCR 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00032 


. 00007 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


0.00125 


0.00070 


0.00010 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


0.00267 


0.00150 


0.00058 


0.00010 


0.0 


0.0 


0.0 


0.0 


70.000 


0.00540 


0.00310 


0.00145 


. 00055 


0.00012 


0.0 


0.0 


0.0 


87.200 


0.00915 


0.00530 


. 00270 


0.00140 


0.00060 


0.0 


0.0 


0.0 



U. 1.1.3-99 



i i\ 



VI 



* 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



m 
en 

T. 
U 
Q 



.10 



.08 



.06 



.04 



DEL SB CDEG3 

50 100 

n i i i i i i ~i 



.02 



illl 



I I I I 



TT 



^F&r*^-Bz*&+**±? 



I l l J. 



\ l r 



~ i 




111 ! 



i I I 



i r 



i i i r 



T 



TT 



-~cr~rTr-fi i rH^ri r?^^""^^ 



i'ii 



i i i I 



_L_L 



-10 



10 
ALPHA 



15 

CDEG) 



20 



25 



30 



CO>FIGLRATI0N 




BASELINE ORBITER VEHICLE 


REFERENCE 0Ih€NSI0NS 




CENTER CF GRAVITY XO » F5 107S.7 IN. 


MING AREA SW « 2630.00 


SQ.FT. 


CR YO » BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MGttNT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB » 1290. J 


IN. 



ENGINEER ^X*L> 
DATE„ft3CE-I^5 



FIGURE 4.1 
EFFECT 



1.3-94 
OF SPEEOBRAKE 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (0EG) 


A 


8 


C 


D 


E 


F 


G 


H 






SPEED 


©RAKE PITCH 


ING MO-tNT 


I NCR 






0.0 


-0.00210 


-0.00236 


-0.00210 


-0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00080 


-0.00090 


-0.00080 


-0.00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00163 


0.00173 


0.00175 


0. CO 160 


0.00134 


0.00097 


0.00057 


. 00029 


45.000 


0.00326 


0.00346 


0.00350 


0.00320 


0.00258 


0.00194 


0.00114 


0.00058 


55.000 


0.00488 


0.00518 


0.00525 


0.00480 


0.00402 


0.00290 


0.00170 


0.00088 


70.000 


0.01145 


0.01135 


0.01125 


0.00980 


. OOBOO 


0.00548 


0.00320 


0.00155 


87.200 


0.02060 


0.02238 


0.02140 


0.01755 


0.01330 


0.00909 


0.00560 


. 00260 



4.1.1.3-100 



U* 



-.C IM 



'1* 



Rockwell International 

Space Division 



MACH NUMBER 



10.000 



00 



U 



.10 



.08 



.06 



.04 



.02 



DELSB COEGD 

50 100 

fill 



I I I I 



-.02 



TTTT 



_L_L 



I I I i 



T i 



J_L 




I I I 



J__L 



I I I I 



TT 



W* < WiflfK - LKL IK LSI. » U 4 H I M 



15 20 25 30 35 HO 

ALPHA CDEGD 



I..1 l 



l l i 



45 



50 



BASELINE 0RBITER VEHICLE 

CENTER OF GRAVITY XO « FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

moment reference zo - w. 375.0 in. 



IT I ON 




REFERENCE DIMENSIONS 




MING AREA SW - 2690.00 


SQ.FT. 


WING SPAN BW - 78.055 


FT. 


M.A.C. CW - 39.560 


FT. 


BCOY LENGTH LB » 1290.0 


IN. 



"'I "I" I I } 

T~T 



T 



U— * M- 



I I 



55 



60 









ALPHA (0EG1 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


CCLS8 <DEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEEC 


BRAKE PITCHING MOMENT 


1NCR 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00097 


0.00057 


0.00029 


0.00010 


0.0 


0.0 


0.0 


0.0 


45.000 


0.00194 


0.00114 


0.00058 


0.00027 


0.0 


0.0 


0.0 


0.0 


55.000 


0.00290 


0.00170 


0.00088 


0.00040 


0.00018 


0.0 


0.0 


0.0 


70.000 


0.00548 


0.00320 


0.00165 


0.00085 


0.00034 


0.0 


0.0 


0.0 


87.200 


0.00909 


. 00560 


0.00260 


0.00130 


0.00055 


0.0 


0.0 


0.0 



ENGINEER. 

»TE_f r _C£: 



v_/ 



FIGURE 4.1.1.3-95 

EFFECT OF SPEEOBRAKE 



4.1.1.3-101 



SL-/2-SH-CCCC 1M 



a 



Rockwell International 

Space Division 



CD 

in 



a 



MACH NUMBER 



15.000 



,10 



.08 



.06 



.04 



.02 



-10 



DELSB CDEG) 

50 100 

| I 1 I l | I I I > | 



i I i I 



_l_L 



! i I 




I I I I 



i I I 



I I I 



-Xr^5r ^«?^frT= 



I i I I 



I 111 



10 

ALPHA 



15 

CDEG) 



20 



25 



I I I I 



I I I 



30 



35 



COWIGURATION 


BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY XO =■ FS 107S.7 IN. 


WING AREA SW = 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU » 78.056 FT. 


MOMENT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW = 39.550 FT. 




BOOY LENGTH L3 * 1290. 3 IN. 











ALPHA 


<DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELSB (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MOMENT 


I NCR 






0.0 


-0.00210 


-0.00236 


-0.00210 


-0.0O105 


0.0 


0.0 


0.0 


0.0 


15.000 


-0 . 00080 


-0.00090 


-0.00080 


-0 . 00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00163 


0.00173 


0.00175 


0.00160 


0.00134 


0.00097 


0.00057 


. 00C29 


45.000 


0.00326 


0.00346 


0.00350 


. 00320 


0.00268 


0.00194 


0.00114 


0.00C5B 


55.000 


0.00488 


0.00518 


0.00525 


. 00480 


. 00402 


. 00290 


0.00170 


0.00088 


70.000 


0.01145 


0.01135 


0.01125 


. 00980 


0.00800 


. 00548 


. 00320 


0.00165 


87.200 


0.02060 


. 02233 


0.02140 


0.01755 


. 1 330 


. 00909 


0.00560 


. 00260 



ENGINEERJ^lD 

date_?-Ql-i3£I 



FIGURE 4.1.1.3-96 

EFFECT OF SPEEDBRAKE 



4.1.1.3-102 



cr 



/ _. - 



ccec im 



'1* 



Rockwell International 

Space Division 



JL 



MACH NUMBER 



15.000 



DELSB CDEG) 

50 100 



m 

T. 
(_) 
Q 



.10 



.08 



.06 



.OH 



.02 



-.02 



TT 



.0 i; — p_p- 



l l I 



i i I I 



fri?5& 



! I 1.1. 



I i 



pT^Ta^ 



i" TT 



.Ta^SB^Ffrft f g£ 



_L_L 



J.-1-.i. 



i I i i 



I I I I 



_L_L 



I I I I 



I I I I 



i I 'I I 



~n 



i i i i 



i i i i 



i i i 



i j i i 



15 



20 



25 



30 



35 

ALPHA 



40 

CDEG3 



45 



50 



55 



60 



COFIOJRATICN 




BASELINE 0RBITER VEHICLE 


REFERENCE Dir€NSIO>6 




CENTER OF GRAVITY XO ■ FS 1076.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO » BL 0.0 IN. 


WING SPAN BW » 78.056 


FT. 


MOMENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 











ALPHA 


(□EG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


"5.000 


50.000 


CELSB (OEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEED 


6RAKE PITCH 


ING MOMENT 


INCR 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00097 


0.00057 


0.00029 


0.00010 


0.0 


0.0 


0.0 


0.0 


45.000 


0.00194 


0.00114 


0.00058 


0.00027 


0.0 


0.0 


0.0 


0.0 


55.000 


. 00290 


0.00170 


0.00088 


0.00040 


0.00018 


0.0 


0.0 


0.0 


70.000 


0.00548 


0.00320 


0.00165 


0.00085 


. 00034 


0.0 


0.0 


0.0 


87.200 


0.00909 


. 00560 


0.00260 


0.00130 


0.00055 


0.0 


0.0 


0.0 



r 



ENGINEER I3$D 
|OATE_3£C£=5S 



FIGURE 4.1.1.3-97 

EFFECT OF SPEEDBRAKE 



v_ 



4.1.1.3-103 



SL '.2-SH-CCeC 1M 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 



20.000 



DEL SB CDEG) 

50 100 

I I I I I I I I i 



Q 




-10 



10 15 

ALPHA CDEGD 



20 



25 



30 



35 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO » FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOTENT REFERENCE ZO « WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW » 2SSO.0O SQ.FT. 
WING SPAN BW ' 78.056 FT. 
M.A.C. CW - 39.560 FT. 
BODY LENGTH LB ■ 1390.3 IN. 



ENGINEER;- _„,_ 



FIGURE 4.1.1.3-98 

FFFFCT OF SPEEDBRAKE 











ALPHA 


IDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15. Q00 


20.600 


25.000 


DELSB IDEG) 


A 


8 


C 


D 


E 


F 


G 


H 






SPEED 


BRAKE PITCH 


ING MCtCNT 


I NCR 






0.0 


-0.00210 


-0.00236 


-0.00210 


-0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


-0.00080 


-0.00090 


-0.00080 


-0.00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


0.00163 


0.00173 


0.00175 


0.00160 


0.00134 


0.00097 


0.00057 


0.00029 


45.000 


0.00326 


0.00346 


0.00350 


0.00320 


0.00268 


0.00194 


0.00114 


0.00058 


55-000 


0.00488 


0.00518 


0.00525 


0.00480 


0.00402 


0.00290 


0.00170 


0.C0088 


70.000 


0.01145 


0.01135 


0.01125 


0.00980 


0.00800 


0.00548 


0.00320 


0.00165 


87.200 


0.02060 


0.02238 


0.02140 


0.01755 


0.01330 


0.00909 


. 00560 


. 00250 



4.1.1.3-104 



cr 



;*ll c im 



'i* 



Rockwell International 

Space Division 



L 



MACH NUMBER 



20.000 



to, 



DELSB CDEGD 

50 100 

I I I I 



IT) 

<Ji 

C 
a 



.08 



.OS 



.04 



.02 



.02 



J_L 



i I I I 




i I "TTT 



i—1 I I l i l I i i i i I i i i i 



i I I I i I I I I I I I 



15 



20 



1. 1. I . ,L 



»n>TJ < j\ % mA + tf l l<L 4«- LKL i tf-iA. M..H M. H 



_L_L 



L I . . I .i— .1 1 I--L 



Mil 



30 



35 HO 

ALPHA CDEGD 



45 



50 



55 



60 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO = BL 0.0 IN. 

MGTENT REFERENCE ZO =■ WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW =• 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BCOY LENGTH LB » I2S0.3 IN. 



0SLS8 <C£G) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



15.000 

F 



20 . 000 
G 



ALPHA (C€G) 



25.000 
H 



30.000 



35.000 
J 



40.000 
K 



45.000 
L.. 



50.000 
M 



0.0 

0.0 

0.0 

0.00097 

0.00194 

0.00290 

0.00548 

0.00909 



0.0 

0.0 

0.0 

0.00057 

0.00114 

0.00170 

0.00320 

0.00560 



SPEEC6RAKE PITCHING MGtE.MT INCR 



0.0 

0.0 

0.0 

0.00029 

0.00058 

0.00088 

0.00165 

. 00260 



0.0 

0.0 

0.0 

0.00010 

0.00027 

0.00040 

. 00085 

0.00130 



0.0 

0.0 

0.0 

0.0 

0.0 

0.00018 

0.00034 

0.00055 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



0.0 0.0 

0.0 0.0 

0.0 0.0 

0.0 0.0 

0.0 0.0 

0.0 0.0 

0.0 0.0 

0.0 0.0 



ENG INZER ££?-& 
OATE.fbiSrliS" 



FIGURE 4.1.1.3-99 

EFFECT OF SPEEDSRAKE 



4.1.1.3-105 



-SM-OCtC 1M 



* 



Rockwell International 

Space Dtvtswn 




JO 15 20 

ALPHA CDEGJ 



25 



30 



35 



COFIGURATICN 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR V0 - BL 0.0 IN. 

MCtCNT REFERENCE ZO - U_ 375.0 IN. 



REFERENCE OlrENSICNS 
WING AREA SW » 2590.00 SQ.FT. 
WING SPAN BW • 78.056 FT. 
M.A.C. CA * 39.560 FT. 

BQOY LENGTH LB - 1290.3 IN. 







KACH NUMBER 


* 


0.250 


0.400 


0.600 


0.800 


0.900 


0.950 


1.050 


1.100 


1 .200 


! 


A 


8 


C 





E 


F 


G 


H 


I 


! '^j-HA (DEO) 




PITCH DAMPING 




-2.000 


-2.69800 


-2.71900 


-2.74800 


-3.00000 


-3.60000 


-3.50300 


-3.25100 


-3.25100 


-3.C5C00 


0.0 


-2.67200 


-2.73700 


-2.82400 


-3.02500 


-3.55400 


-3.58100 


-3.27700 


-3.27700 


-3.075CO 


2.000 


-2.74800 


-2.76900 


-2.79800 


-3.05100 


-3.80600 


-4.46600 


-3.50500 


-3.40300 


-3.05100 


4.000 


-2.72000 


-2.75400 


-2.82300 


-3.22700 


-4 . 33600 


-5.39600 


-3.68100 


-3.52S00 


-3. 12500 


6.000 


-2. 64 700 


-2.71100 


-2.79800 


-3.50300 


-4.56500 


-4.15700 


-3.30300 


-3.40400 


-3.30700 


8.000 


-2.26900 


-2.39800 


-2.57200 


-3.63000 


-4 . 08400 


-2.87400 


-2.16700 


-2.92400 


-3.83200 


10.000 


-1.68900 


-1.71700 


-1.94100 


-3.05100 


-3.20200 


-2.09300 


-1.23500 


-1.84000 


-1.46800 


12.000 


-1.16100 


-1.20300 


-1.26100 


-2.52100 


-2.77300 


-1.71400 


-0.95700 


-1.00800 


-1.00800 


14.000 


-0.93300 


-1.04100 


-1.18500 


-2.34400 


-3.00000 


-1.84100 


-1.58800 


-1.33600 


-1 .23500 


16.000 


-0.80700 


-0.97900 


-1 .20900 


-2.52100 


-4.03400 


-3.07600 


-2.62300 


-2.21800 


-1.71500 


IS. 000 


-0.83200 


-1.19900 


-1.68900 


-3.45300 


-5.72300 


-4.91500 


-3.75600 


-3.10000 


-2.04200 


20.000 


-1.15900 


-1.80700 


-2.67200 


-6.00100 


-7.95600 


-7.05900 


-5.04200 


-4.03400 


-3.02400 


22.000 


-I. 15900 


-1.80700 


-2.67200 


-6.00100 


-7.96600 


-7.05900 


-5.04200 


-4.03400 


-3.C2-C0 


24.000 


-1.15900 


-1.80700 


-2.67200 


-6.00100 


-7.96500 


-7.05S00 


-5.04200 


-4. 03400 


-3.02"00 


26.000 


-1.15900 


-1.80700 


-2.67200 


-6.00100 


-7.96600 


-7.05900 


-5.04200 


-4.03400 


-3.C2M3C 


28.000 


-1.15900 


-1.80700 


-2.67200 


-6.00100 


-7.96600 


-7.05900 


-5.04200 


-4 . 03400 


-3.02400 


30.000 


-1.15900 


-1.80700 


-2.67200 


-6.00100 


-7.96600 


-7.05900 


-5.04200 


-4.03400 


-3.02^00 


32-000 


-1.15900 


-1.80700 


-2.57200 


-6.00100 


-7.96600 


-7.0590C 


-5.04200 


-4.03400 


-3.32-00 i 


ingi^er 




FIG 


URE 4.] 


. 1 . 3- 10 














OATE. 



PITCH DAMPING 



4.1.1.3-106 



CCLC IM 



'1* 



Rockwell International 

Space Division 



L 



G 




10 15 ao 

ALPHA CDEG) 



c 













CONFIGURATION 














BASELINE ORB1TER VEHICLE REFERENCE DlhCNSIONS 










CENTER CF GRAVITY XO » FS 1076.7 IN. WING AREA 


SW - 2690.00 SO. FT. 












OR 


YO - 8L 


0.0 IN. WING SPAN 


BW = 78. 


056 FT. 










MCtENT REFERENCE 


ZO = WL 


375.0 IN. M.A.C. 


CW = 39. 


560 FT. 
















BODY LENGTH LB = 1290.3 IN. 




























MACH NUhBER 


1.300 


1.500 


2.000 


3.000 


4.000 


5.000 


8.000 


10.000 


20 . 000 


ALPHA <OEG) 


J 


K 


L 


M 


N 





P 





R 




PITCH DAMPING 








-2.000 


-3.25200 


-3.20000 


-2.40000 


-1 .80000 


-1.50000 


-1.60000 


-0.27800 


-0.27800 


-0.27800 


0.0 


-3.22700 


-3.10000 


-2.40000 


-1.80000 


-1.50000 


-1.60000 


-0.65300 


-0.65300 


-0.65300 


2.000 


-3.25200 


-3.10000 


-2.40000 


-1.80000 


-1.50000 


-1.60000 


-0 . 87600 


-0.87600 


-0.87600 


4.000 


-3.22700 


-3.10000 


-2.40000 


-1.80000 


-1.50000 


-1.60000 


-0 . 99800 


-0.99800 


-0.99800 


6.000 


-3.40400 


-3.10000 


-2.40000 


-1.70000 


-1.50000 


-1.60000 


-1.12200 


-1.12200 


-1.12200 


8.000 


-3.63000 


-3.20000 


-2.40000 


-1.70000 


-1.50000 


-1.60000 


-1.34500 


-1.34500 


-1.34500 


10.000 


-2.79800 


-3.00000 


-2.20000 


-1.70000 


-1.50000 


-1.60000 


-1.72200 


-1.72200 


-1.72200 


12.000 


-1.05900 


-1.20000 


-1.90000 


-l.SOOOO 


-1.50000 


-1 .50000 


-1.99300 


-1.99300 


-1.99300 


It. 000 


-1.23500 


-1.00000 


-1.70000 


-1.80000 


-1.50000 


-1.60000 


-2.26700 


-5.26700 


-2.26700 


16.000 


-1.81500 


-1.10000 


-2.00000 


-1.90000 


-1.50000 


-1.60000 


-2.49000 


-2.49000 


-2.49000 


ie.oco 


-2.19300 


-1 .50000 


-2.40000 


-2.10000 


-1.50000 


-1.60000 


-2.61400 


-2.61400 


-2.61400 


20.000 


-2.52000 


-2.20000 


-2.60000 


-2.30000 


-1.80000 


-1.60000 


-2.63800 


-2.63800 


-2.63800 


22.000 


-?. 52000 


-2.20000 


-2.60000 


-2.30000 


-1.90000 


-1.70000 


-2.51100 


-2.51100 


-2.51100 


24.000 


-2.52000 


-2.20000 


-2.50000 


-2.40000 


-2.00000 


-1.80000 


-2.329C0 


-2.32900 


-2.32900 


26.000 


-2.52000 


-2.20000 


-2.20000 


-2.40000 


-2.10000 


-2.20000 


-2.20200 


-2.20200 


-2.20200 


29.000 


-2.52000 


-2.20000 


-1.80000 


-2.00000 


-2.10000 


-2.50000 


-2.20200 


-2.20200 


-2.20200 


30 . 000 


-2.52000 


-2.20000 


-1.10000 


-1.50000 


-2.10000 


-2.80000 


-2.20200 


-2.20200 


-2.20200 


32.000 


-2-52000 


-2.20000 


0.0 


-1.00000 


-2 . 1 0000 


-3.10000 


-2.20200 


-2.20200 


-2.20200 


ENGINEER 




FIC 


>URE 4.] 


. 1 . 3-101 










DATE 






PI 


TCH DAMPING 




















4.1.1.3- 


■107 











I 72-SH-ocec 1M 



* 



Rockwell International 

Spaca Ovision 




IF 



K !l (i^).(,-K„)(^ r ) 



^ Cm q 5l =ioo° 

W* 13-75° 



NOTS: 1. For normal simulations, use K s , - 0.5 

2. For sensitivity studies, assisne K 5| can be either or 1. 



i 


mach mj-ber 


i 


0.250 


0.400 


0.500 0.300 


0.900 0.950 


1.050 


1.100 1.200 


2.000 




A 


3 


C 


E f 


G 


H 1 


J 


U..1CS3I- 




__ 


S3 - SF PITCH OAWP1N3 [NCR£reNT 








-2. CCO 


-0.10000 


-1.22000 


-1.70000 -1.40000 


-1.20000 -3.10000 


-1.70000 


-1.40000 -o.soooo 


0.0 


j a.o 


-0.50000 


-1.42000 


-1.70000 -1.40000 


-1.20000 -3.10000 


-1.70000 


-1.40000 -0.90000 


0.0 


' 2.000 


-o.soooo 


-1.50000 


-1.80000 -1.4C000 


-1.20000-10.00000 


-2.30000 


-1.70000 -1 .20000 


0.0 


l 4.000 


-0.30000 


-1.67000 


-2.50000 -l.HOOOO 


0.0 -2.30000 


-2.30000 


-2.00000 -[.80000 


0.0 


j 5.000' 


-0.30000 


-i. 65000 


-1.00000 -1. 40000 


-1.40000 0.70000 


0.0 


-0.50000 -l .30000 


0.0 


! 3.000 


-o.scooo 


-1.25000 


-1.30000 -2.00000 


-0.70000 2.50000 


1.00000 


-0.50000 -3.30000 


0.0 


10. 000 


-0.50000 


-i.10000 


-1.90000 -2.70000 


-2.50000' 1.30000 


-0.20000 


-1.50000 -4.30000 


0.0 


13.000 


-t. 70000 


-1.35000 


-2.20000 -2.70000 


-1.40000 2.50000 


1.70000 


1.10000 0.0 


0.0 


14.900 


-1 .90000 


-0.40000 


O.SOOOO -0.70000 


-1.40000 3.90000 


1.40000 


-0.20000 -2.70000 


0.0 


16.000 


-2.50000 


-2.65000 


-2.50000 -1.90000 


-1.30000 -0.50000 


-1.10000 


-1.60000 -2.30000 


0.0 


13.000 


-1.90000 


-2.50000 


-2.30000.. -2. 10000 


-0.60000 4.10000 


2.00000 


0.40000 -4.10000 


0.0 


20.0C0 


-2.20000 


-3.35000 


-4.00000 4.50000 


9.70000 6.20000 


I .50000 


-1.00000 -6.00000 


0.0 






FIGURE 4. 1.1.3-102 

PITCH (DAMPING INCREMENT 



t.1.1.3-108 



£ E ; £ - s h - c ;. l c 



M 



'1* 



Rockwell International 

Space Division 





ccNnouuriON 


a»sn.ifc o*bitu» 


*hicu 


«RK[ OlrOfllOC 


ctxnn <r uuvm m 


• r? 107S.7 IN. 


-IKO j<ca a ■ 2S90.:o sa.rr. 


CR 1*0 


• O. 0.3 IN. 


uiw> ?w au • to.osb rr. 


■OOT SE7COCX a 


- u. 375.3 in. 


n.A.e. oj ■ s.sso rr. 
9o?i' -star* 'j • '290.3 'n. 



E \4-----K-.K^ VT 



VFV 



^n; 



V3i 



i\\ 



3SM 



--K^- 



^ 




o.a 
MACH 



1.3 

NUMBER 













«x irect 










a. ao 


3.800 


o.aoa 


3.300 


3.950 


1.30 


1. 100 


1.209 


1.300 


SJ* T'. 


a 


9 


c 





C 


r 


s 


- 


1 








"• tFHH. 


"JK£ :CR L 


'.rr: 3.3» 








3.3 


i.ooato 


1.30000 


i. cocao 


1.30003 


I.C00OO 


1.30C00 


1.30000 


1 . 30300 


1.30000 


ioo. oca 


9.98987 


0.9BB57 


0.9BE0 


9.99590 


3.39550 


0.39557 


0.99953 


0.9BJI3 


3.39850 


200.300 


9.99333 


0.38313 


3. SIM] 


0. 99100 


3.99100 


3.38073 


0.39107 


0.39B2T 


0.99320 


3oa.no 


9.99000 


0.99870 


3. 98980 


3.9B7H0 


i.sasso 


3.33580 


3.5SB80 


0.988*0 


3.38980 


"00.000 


0.9B9S7 


0.99927 


33840 


0.90323 


9.38200 


3.30107 


3.9B13 


0.3M3 


3.990*0 


»0. 130 


0.9BJ33 


9.38233 


3.S8IC0 


1.97S00 


3.r~;o 


3. 5-533 


3.5T7ST 


0. 59097 


3.SB3SD 



0SAR CPSF1 
o as 500 





















| 1 1 1 , | , 1 ll| 




1 1^1 i * 


^■IHJ" 














F*<I-^r;tr^ 










v. S* r***--"^^ki*K— — - 




-^i^T-i^rj^n. .^^l_ 
























\ >* 




*■-**" *~ 










- 


l*. ■ IJ 


„ 




^r' ifcC"' ^a 














_ 






























\ ^ 


\^* 
















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/ 
















n «m 


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s 














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- 




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3 
















- 




; 




















\ 




: 




















\ 
























- 


0.970 


"l : i, i 


,1.U1 


I I I I 


1 1 > • 


1111 


i'ii. 


11'! 


.'Ill 


,1 ! 1 1 


MM 


, L,L 111 



5 S 7 t 

MACH NUMBER 





•UOi -US]) 




1.500 


2.300 


2.500 


3.000 


3.J0O 


h.300 


5.000 


1.300 


10.300 


ow» pyi 




K 


I. 


•1 


H 


1 


» 





H 








tm xrnwi. '<ta. '.at t. 


:m 9.3*: 








0.0 


1.30000 


1.00008 


1 .00000 


1 .30000 


1.30000 


1.CO030 


1.30000 


1.00000 


1.30C00 


ICO.OOO 


0.9B7Z3 


9.98903 


0.99893 


9.99980 


0. 99900 


9.39913 


9.99H7 


0.98B33 


a.'fwi i 


200.300 


0.99V*7 


0.38507 


9.99707 


9.99780 


0.99800 


9.99897 


9.99853 


9.3S857 


3.UMD> 


3D0.0OO 


9.99170 


0.95*10 


0. 39560 


0. 988*0 


3.99700 


9.9TMI 


9.997B0 


0.90800 


<>.'j68nfl 


"00.300 


9.9B993 


0.98313 


9.99HI3 


0.99530 


3.99500 


3.39953 


3.39707 


0.97733 


g.udns 




3.3BI7 


3.S9017 




3.99*00 


3.99500 


3.59557 


3.<S"J33 


3.99S87 


3.S9SB7 



date.v-.si-xs; 



i*.1.1.3-IC3 



FIGURE 
FLEX/RIGID NORMAL FCRCE CCR LI FT 5 SLCPE WITH ALPHA 



.1.3-1C9 



CL72-SH-CC6C 1 M 



0J> 



Rockweil International 

Space Division 



SASC!*< -^Wlld ^CXIQX V4>LHk>CE Cf«fil»6 

cejvttb of ou»m >o • rs ions.? :n. «i»o vc» * • ssso.oo aa.rr. 

3* 10 • a. 0-0 IN. 4IhO SP»H & ■ "3. CM rr. 

forcKT <juk { as • n. rrs.a ^H. ™.i.c. en ■ s.ao rr. 



f^: 



EMS 



csar ' ?sn 

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: i ' — r - 1 — i — i — 1 




0.3 
100.300 
MO. 000 

sn.:oo 
wqo.ooo 

*so.ooo 



i.aoooo 

0.9B2XS 

0.9BM7 

0.»TOI 

0.SS33 

HIP 



t.ooaoo 
3. am 

J.J~O0 
3.3WD 



1.00000 

j.stwo 

J. MM 
3.93.C0 
0.912C3 
■).s9C00 



i 20000 i 

J.TJUO ! 

3.3130 ! 
l.tM j 



cocoa I 

3.3JM7 
: 59CC3 



i. cocao 


i.oooao 


j.ssorr 


3.36010 


3. SOTS 


3.S310O 


3.3110 


o.sona 


:.>i»7 


3.3^00 


:.3C'.93 


3.3CK0 



l.oooco 


i.oaooo 


0.3E3M) 


0.98ED 


a.9?-80 


0.331V7 


0.3B730 


a.dU'W 


o.3**o 


Q.a&iJJ 


o.aifoo 


f 0.S2S57 




tNG 

OA' 



*£*?£=%£: r_ex i ble/r^g^1lev'on Pitching moment effectiveness. 



U. 1.1. 3-110 






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4.1.1.3- 111 



'1* 



Rockwell International 

Spaca Division 



IT 
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Rockwell International 

Space Division 



coricuuricM 
a*sn.:x obsiter chicle <^ref04X sitosiaa 

cemtui or ctuvt-nr a . rs iot».7 w. urns >*& sj - aao.co sa.rr. 
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emjiics^*^ F IGURE 4.1.1.3-1C7 

WG.4SXZ25. FLEX PITCHING MOMENT {NCR. AT ZERO ANGLE CF ATTACK 



i. 1.1. 3-H3 



sr72-sf-!-ocec im 



01* 



Rockwell International 

Space Division 



txwiajuncN 


a*au»c ciwitct -cxiaj; 


VFETOCE 0!WJ«l»« 


cchte* cr 3Uvitv no - rt ta7».7 m. 


uihj *c* sj • asso.jo so.rr. 


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o.a i. a 

MACH NUMSER 



G8AR CPSF} 
290 MO 























1 1 1 1 | , , , 1 | 




=\ 


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rw-.^rrs J^ST FIGURE 4.1.1.3-1C8 

SjJS^H^ FLEX AERODYNAMIC CENTER SHIFT Ca MAC- = FVD SHIFT] 



^.1.1.3-lL 



r l 



lC IM 



'1* 



Rockwell International 

Space Division 

L 



ALPHA CDEG) 

-20 20 40 

1 — i — [~r— l — I — l — l 



CD 
_J 

u 

a 



-.001 



-.002 



.003 



.004 



.005 



-20 




J I L 



i — i — r 



J L 



140 



THETA C0EG3 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE D^NSJONS 




CENTER CF GRAVITY XO = F5 107S.7 IN. 


WING AREA SW « 2690.00 


SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BW - 79.055 


FT. 


MCfENT REFERENCE ZO - WL 375.0 !N. 


tt.A.C. CW = 39.560 


FT. 




BCOY LENGTH LB = 1290.3 


IN. 











THETA 


(DEG) 








0.0 


1.000 


4.000 


10.000 


23.000 


53.000 


83.000 


98.000 


ALPHA (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 




LAND 


ING GEAR P. 


M. INCRE^EN' 


T 






-10.000 


0.0 


-0.00024 


-0.00080 


-0.00130 


-0.00210 


-0.00319 


-0.00409 


-0.00459 


-5.000 


0.0 


-0.00022 


-0.00074 


-0.00120 


-0.00194 


-0.00296 


-0 . 00379 


-0.00425 


0.0 


0.0 


-0.00021 


-0 . 00070 


-0.00114 


-0.00184 


-0.00290 


-0.00359 


-0 . 00403 


5.000 


0.0 


-0.00022 


-0.00073 


-0.00118 


-0.00191 


-0.00291 


-0.00373 


-0.00419 


10.000 


0.0 


-0.00024 


-0.00080 


-0.00130 


-0.00210 


-0.00320 


-0.00410 


-0 . 00460 


15. COO 


0.0 


-0.00025 


-0.00083 


-0.00135 


-0.00218 


-0 . 00332 


-0.00425 


-0.00477 


20.000 


0.0 


-0.00018 


-0.00062 


-0.00100 


-0.00162 


-0.00246 


-0.00316 


-0.00354 


25.000 


0.0 


-0.00007 


-0.00023 


-0.00037 


-0.00060 


-0.00092 


-0.00118 


-0.00132 



ENGINEEI 
DATE 






L AND ING 



FIGURE 4.1 
GEAR PITCHING 



. 1 . 3- 109 
MOMENT COEFFICIENT 



INCREMENT 



4.1.1.3-115 



LL 



ih-OCLG llVi 



<Qt 



Rockwell International 

SpacaOJvnion 




Landing Gear Down 



^ C ' T, 3»ouN0~ CT,l G*0UN0 Cm faee 

"FSCT 5T»l*M 



EfMCT 



5 s -40.000 




5„ = -U.7« 



fc 



CONFIGURATION } 

lASClUC MUTCH itHICU j 

o« ! T .*« 0.30 I 

•omimt iimmnci '£.'«« 375.J8 j 

MFEUMt 31«KIMS 

Aio w U 95.3 Oli.' 

i»h v.» 71.351 i, 

•ac ..■ 11551 «. 

>OOT LIHOrM l« • IJMlJM ■« 



8 Si = All 



l-i^l 




-.10 



0.2 O.H O.S 0.8 

HEIGHT/SPAN 



1.0 



1.2 



I.H 



1.6 



X«f«r«ii<« fvtnl 




<^M 



MHOHV" 
h/b 




Angle of Aft 


ack, GL ~ Degrees 


A -H.000 


1 0.0 


c H.000 


3.000 


( 12.000 


f 16.000 | a 20.000 


1 


ncremental Pitching 


Moment Coefficient , &Cm<mtt} sfmct 


0.025 


0.06000 


0.05470 


O.O 1 * '♦00 


0.02400 


0.02400 


. 00670 


-0.07i00 


0.0SO" 


0.07340 


. 06270 


. 05740 


0.0507U 


. 05070 


0.04270 


0.00540 


0.100 


0.08010 


0.07210 


. 0655O 


1 . OH 950 


. 04550 


0.04010 


0.02550 


0.200 


. 04560 


. 03390 


0.02560- 


. 1 890 


. 00960 


-0. 00240 


-0.00790 


0.30O 


0.02040 


0. 01770 


0.0 


0.00570 


0.00570 


-0.00760 


-0.01430 


o.sao 


0.01 130 


. 1 1 30 


0.0 


0.00330 


0.00330 


-0.00340 


-0.00740 


1.0 00 


0.00400 


0.00400 


0.0 


0.0 


0.0 


0.0 


-0.00300 


1 I.SOO 


o.o 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



.' J 



OAfl '■/ 



-*/7"» 



Figure 4.1.1.3-UO 

GROUND EFFECT 



4.1.1.3-114 



SD72-^H-CU.C iivi 



J 



4* 



Rockwell International 

SpacsCtvaicn 



Landing Gmar Dawn 



EFFfCT EFFKT STREAM 



&°^t 



<Z 



CONFIGURATION 

IWUK 0IIITE1 r£HICl£ 

eiHru o* oiA.irr /«,■>! 1071.71 
o* j '. « u l.Ot 

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UFEUXCl 1IMEMI0IK 

am* w«ZIH.0Mta' 

sum v.» 71.351 t 

mot iitaant L, ' t!tt.3M : 




0.2 



a. 1 * 



O.S 0.8 t.O 

HEIGHT /SPAN 



1.6 




_Xtf«r«*<a Point 

»., h/b 

X. 1306.84 
Z, 282.71 



HIIGHT/ 
h/b 




Angle of Art 


ock, Ct ~ Degrees 




A -H.000 


» 0.0 


c H.000 


o a. oao 


• 12.000 |f 16.000 


G 20.000 


1 


ncramenta 


1 Pitching 


Moment 


Coefficient , ACrv; 


»IHO EFFfCT 


0.029 


0.10930 


0. 09*60 


. Q9060 


0.08800 


0.08130 


0.01730 


-O.O'+SVO 


0.0*50 ' 


0. 10930 


. 09860 


0.09330 


0.08930 


0.08260 


. 03590 


-0.01H70 


0.100 


0.10390 


. 09590 


0.08650 


0.08120 


0.07190 


0. 03850 


o.omso 


0.200 


O.O^O 


0.03710 


. 02760 


. 02380 


0.01 0H0 


•0.00160 


-0.00*20 


0.300 


a. 01560 


0.01560 


0.00630 


0.0 


-0.00570 


-0.00700 


-0.00700 


0.500 


0.00870 


0.00870 


0.30210 


0.0 


-0.00330 


-0.00330 


-0.00330 


1.000 


0.00500 


0.00500 


0.0 


0.0 


0.0 


0.0 


0.0 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



- i 



ENGINEER'^ 
PATE- 47 
SJVISEO- 



■iUL. 



Figure 4-1.1.3-111 

GROUND EFFECT 



4.1.1.3-117 



i ,„ ( 



0$ 



Rockwell International 

Space Otaswn 



Landing Gear Down 



EFFECT £?MCT 3TREAM 



CONFIGURATION 

liSUUE 3MITEI VCMICU 
Clf'll of OJlAvirT 



I !.•«* i75.M 



UF(U1CE 3IMCXSI0IIS 



I-^S 




=nV 



0.2 0.H 0.6 0.8 

HEIGHT/SPAN 



1.0 



1.2 



..•♦ 



1.6 




i„ h/b 

X„ 1306.3' 
Z« 282.71 



HEIGHT/ 
•VAN 

h/b 




Angle of Attoek, at — Degrees 






A-H.000 


, 0.0 


c H.000 


9.00O 


( 12.000 | 


• 16.000 


G 20.000 


1 


ncrementa 


Pitching 


Moment 


Coefficient .^Cm G 


»NO !«»ECT 


0.025 


0. 19660 


0. 13260 


0. 15860 


0. 11 060 


0.08530 


G.0i73u 


-0.06000 


0.050 ' 


0. 17330 


0. 15730 


. 1 3590 


. 09H60 


. 07V6O 


0.01730 


-0.03610 


3.10O 


0.12250 


. 1 1 320 


0.09720 


. 06790 


. 05320 


0.01590 


-0.01750 


0.200 


0.05960 


0.05580 


0.0*51O 


0.03310 


0.02510 


0.010*0 


-0.00290 


0.300 


0.03030 


0.03030 


. 02360 


0.01700 


0.01300 


0.00900 


0.00233 


0.500 


0.019H0 


0.0l9<40 


O.OIH10 


0.00870 


0.007*0 


0.00*70 


0. 00*70 


1.000 


0.00800 


0.00800 


0.00500 


0.00500 


0.00500 


0.00300 


0.00300 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



ENGINEER '- 
OA.'E _2" 


■7 


) 

-7 


_Z_ 


*EVISI0= 


^. ,,. 



Figure 4.1.1.3-112 

GROUND EFFECT 



4.1.1.3-H* 



J 



O "i - «- 



<V r 



CCCC IM 



* 



Rockwell International 

Soaca dvision 




Landing Gear Down 



[MtCT IFMCT 5TRSAM 



5 # = -15.000° 





8„ = -11.7' 



^ 



CONHOUHATICN 

IISEIHE JMITEii VEHICU 

ciniii Of 3»»»itt |i,iii [07I.j*9 

«M«[ IIMHNCI ll,'* 375JI 

UFEM1CE 3I««I0« 

I'M k.« JU5I h 



MOT HMOrM l t ' 



JtSH * 



5 3t =Ul 



AC^. t .1 




o.a 



O.H 




O.S 0-8 t.O 

HEIGHT /SPAN 



«.r h/b 

X. I JOS. 34 
Z.. 282.71 



1.2 



l.<* 



h/b 




Angle of Att 


oek, a — 0«gr««» 


A -H.000 


. 0.0 


c H.OOO 


3.000 


1 12.000 


f 18.000 


(-20.000 


! 


ncremantal Pitching 


Moment 


Coefficient , ACnv;» N o »F»SCT 


0.029 


0.16930 


0.15600 


0.13730 


0. 10800 


0.06130 


-0.01070 


-0.07730 


0.WO ' 


0. 1*800 


. 1 3600 


0.11370 


0.09200 


0.05200 


-0.00530 


-0.05330 


0.100 


0.10930 


0.10130 


0.08670 


0.0653O 


0.03730 


0.00130 


-0.02530 


0.200 


O.OS330 


0.05070 


0. 04000 


0.02600 


0.01*70 


0.00270 


-0.00930 


0.300 


. 02670 


0.02530 


0.02000 


0.01200 


0.0 


-0.00800 


-0.00800 


0.500 


0.01330 


0.01>*70 


0.01070 


0.00530 


0.0 


-0. 00*00 


-O.OOSOO 


1.000 


O.OOSOO 


0.00500 


0.00300 


0.0 


0.0 


-0.00200 


-0.00200 


1.500 


J 0.0 


0.0 


0.0 


J 0.0 


0.0 


0.0 


0.0 



ENOINttlt', 

OAT J- ± 

MVISW 



J' 



■/#--?7 



Figure 4.1.1.3-H3 

GROUND EFFECT 



1.5 



4.1.1.3-H9 



i ,v: 



^"i-^ Rockwell international 

Space Ch/wcn 




5,= 



-10. ootr 



Landing Gear Down 



^ Cm 3»OtJN0" m G»OUHO Cm f*tt 



EFFECT 



EFFECT 



STREAM 




5 1F = -U.7« 



CONFIGURATION 

msjuie omitei timit 

ciHMi o» oj»«ii-» i >,"i I07IJJ 
oi <'. *» 3.CQ 

-0««NT IIMtfMCl 'i,"«l J7S.J1 

am* w*2i!9.39l>'' 

■uc ,. > I1SS» * 

tear iimoth i, » ICIIJO) >. 



^ 



8 S ,= All 



*=■*, 




-.05 



-.10 



I ! I 



1 i I I i ! i I i i I i ~1 i i I i r 



i I I 



J ! L 



0.2 O.H 0.6 0.9 1.0 

HEIGHT/SPAN 



1.2 



l.H 



1.6 




« A«J«r«nca Paint 

r„ h/b 

X. 1504.3* 
Z. 282.7! 



HEIGHT/ 

•Van 
h/b 




Angle of Alt 


ae!t, at ~ Degree* 


A -*».00O 


s o.o 


c «».000 1 


a.ooo 1 


; 12.000 |f 13.000 G 20.000 


1 


ncremental Pitching 


Moment 


Coefficient , AOm^^o sffec* 


0.023 


o. m««7o 


0.12620 


0. 10910 


0.07890 


0.03900 


-0.03300 


-o.oebor. 


0.050 " 


0. 12H80 


0.10900 


0.09460 


0.06430 


0.03100 


-0.02100 


-0.06400 


0.100 


0.09170 


. 08250 


o.oea ia 


. 04570 


0.02070 


-0.01200 


-0.03700 


0.200 


o.o^eoo 


. 0H27O 


0.03350 


0.02160 


0.01000 


-0.00500 


-0.01700 


0.300 


0.02520 


0.02130 


0.01470 


0.01080 


0.00700 


-0.00400 


-0.01000 


O.SOO 


0.007VO 


0.00740 


0.00350 


0.00350 


0.00350 


0.0 


-0.00200 


1.000 


0-00500 


0.00500 


0.00200 


0.00200 


0.00200 


0.0 


0.0 


1.500 


0.0 


0.0 


0.0 


CO 


0.0 


0.0 


0.0 



ENGINE!* 
OAT! ___ 
*IVISED< 



J. 



4-/*/- 77 



Figure 4.1.1.3-1^* 

GROUND EFFECT 




4.1.1.3-120 



* 



Rockwell International 

Space Drvwion 



Landing Gear Oown 



/£ 




= C„ 



..-c, 



5MICT e"!CT ST«*M 



"* TY 




CONMOURATION 

I1SEUIE JIIITH HHKU 

cimtii at ai»»irr 1 1,"» IQJI.J9 
o« ! '. « u J.OO 

■OMM IIIIHKI <£,«»» J7J.3J 

ufchici atMCssiaas 

smn v»» N.35I '. 



... ]1SM* 

nor iihorx i, • IIJCJO) ■. 



s, 



= -5.000° 



5„ = -11.7' 



S Si =All 



ACn>. e 




0.2 



0.H 




0.6 0.8 1.0 

HEIGHT/SPAN 

.«,< h/b 

Z„ 282.71 



1.2 



l.H 



1.6 



.•VAN 

h/b 



Angle of Attqcit, « ~ Degree! 



.000 



0.0 



c H.000 J Q 8.000 



; 12.000 f 18. OOP 



.20.000 



Incremental Pitching Moment Coefficient , ACmcaNO ir*i<r 



0.023 
0.05O ' 
0.100 
0.200 
0.300 

a. 500 

1.000 
1.500 



0. 15000 
0.12830 
0.090H0 
O.O^SVO 
0.02800 
0. 01020 
. 30250 
0.0 



0. 131 10 

0.11080 
0.07830 
0. 0*030 
0.02260 

0.01020 
0.00250 
0.0 



0. 10940 

a . 090S0 

0.06340 
0.03080 
0.01720 
0.01020 
0.00250 
0.0 



I 



0.07500 
. 06200 
0.0X300 
0.022C0 

o. a i ioo 

0.00610 
0.00200 
0.0 



0.03240 
. 32560 
0.01740 
0.01060 
0.00770 
0.00610 
0.30200 
0.0 



-0.03650 
-0.03650 
-0.02720 
-0.01 1 10 
-0.00710 
-0.0O33O 

0.0 

0.0 



-0.09330 
-0.07030 

0.04070 
-0.01920 
-0.01250 
-0.007X0 

0.30300 

0.0 



ENGINKX' 
3ATT 

mvisio- 



■- i 
r 



'■/•/*¥■ 77 



Figure 4. 7 -«l»3~115 

GROUND EFFECT 



4.1.1.3-121 



SD 72-SH-CCtC 1M 



0^ 



Rockwell (ntemational 

Spaca Civrsicn 



CCNFIGU8ATION 

iSUlU IMirU iSHlCU 

SINfll 01 CJ*»(TT 



•cmint lcriifMci li*>«* J75.38 j 

in* v.» rs.sjs i- 




^ 



0.6 0.8 1.0 

HEIGHT /SPAN 



l.S 




. Iilirixt P» 


<ir 


»,r h/b 




X. 1506.3* 




I. 232.71 





OaTE _£ 



/ * 



^■V" 77 



V 



HUGHT^ 
XJ>AN 

h/b 




Angle of Alt 


oek, a — Degrees 


A -M.000 1 


, 0.0 


c h.qoo 


8.00O 


; 12.000 


t 18.000 


G 20.000 


1 


ner«m«nta 


1 Pitching 


Moment Coefficient , ^On^j N0 jt» !CT 


0.025 


0.1>»300 


0.10700 


0.08600- 


0.04300 


-0.02800 


-0.05200 


-0.08400 


0.920 ' 


0. 10700 


0.08700 


. 06700 


0.03300 


-0.01700 


-0.03730 


-0.06150 


0.100 


0.07200 


0.0570O 


0.04600 


. 02230 


-0.00650 


-0.02500 


-0.34 180 


3.200 


0.03550 


0.02910 


0.02130 


0.01070 


-0.00350 


-0.01720 


-0.02570 


0.300 


0.01850 


0.01460 


O.OIIMJ 


0.00650 


-0.30240 


-0.01220 


-0.01880 


0.3QO 


0.00660 


. 00670 


0.00400 


0.00400 


. 00020 


-0.00570 


-0.00960 


1.0 00 


0.00400 


0.00400 


0.00200 


0.30200 


0.0 


-0.00200 


-0.00400 


1.500 


0.0' 


0.0 


j 0.0 


0.0 


0.0 


0.0 


0.0 



Figur* 4.1.1.3-H6 

GROUND EFFECT 



4.1.1.3-122 



K^S 



* 



Rockwell International 

Spaca Division 




Landing G«ar Down 



^ Cm 3RCU*<r n, G»QUNo" C ' n '«« 



ifncT 



SFfECT 



STMAM 




5.= 5.000 ( 



8„ = -U.7* 



CONFIGURATION 

I1SEUH MIITEI <CHICU 

ciniii o# 3J**irr , mh I07IJ8 

3« J », t u 0.0J 

OOM4HI HHIIMC1 I I."* 37LM 

lEFCH'Ct 3IHIH10K 

iHut t.* ;j.osi >■ 

«< .. . :iiM <. 

wot iiMarM i« • 12JI.3M • 



5 $i = All 



^ 



bGPzt 




-.10 



0.2 



0.4 



0.6 




0.8 
HEIGHT/SPAN 

_(tf*'«"c> Faint 

f., h/b 

X. '.S06.3A 
Z. 282.71 



1.0 



1.2 



I.H 



















•Van 

h/b 




Angle of Aft 


ock, a — Degrees 




A -H.0OO 1 


• o-o 1 


c H.000 


g a. ooo 1 { 12.000 


r 16.000 


a 20.000 


| lncr«m«nta 


Pitching 


Moment Coefficient , ^Cm<3 


»NO IFMCT 


0.029 


0.08600 


0.06700 


0.04700 


0.01700 


-0.02800 


-0.06000 


-0.09000 


o.no ' 


0.07200 


. 05700 


0.03300 


0.01360 


-0.02120 


-o.ose^a 


-0.06620 


0.100 


0.05500 


0.04140 


0.02670 


0.00710 


-O.0155Q 


-3.03390 


-0.04*10 


0.200 


0.33110 


0.02060 


0.01190 


0.00240 


-0.00930 


-0.01770 


-0.02200 


0.300 


0.01970 


0.01220 


0.0C6H0 


-0.00020 


-0.00790 


-0.01080 


-0.01310 


0.SQ0 
1.300 


0.00860 


. 00520 


0.00320 


-0.30010 


-0.00290 


-0.00690 


-O.OC6>*0 


0.00100 


. 00050 


0.00050 


0.0 


-0.00200 


-0.00400 


-0.00"00 


I.SOO 




0.0 


0.0 


o.o 


0.0 

- 


0.0 


0.0 



INGINH* 

oaii-__2, 
mvisio 



S. 



-"V- 77 



Figwre 4.] .1.3-117 

GROUND EFFECT 



4.1.1.3-123 



SD'ja-SH-ocec im 



tf> 



Rcckweil International 

Spac* Civaion 




Landing G«ar Down 



EFFECT 



m^„„.,..„ ^"^ouno ^""FseE 



SFMCT 



STREAM 




3.= 10.000' 



S„ = -U.7« 



^ 



\ 



CONFIGURATION 

I1SUIU HUTCH *EH)CL£ | 

CJNrn Qf GJAvirr < **"! 1073.73 i 

o« J », »u 9.31 ' 

•oww iffiifxei (!,>«* 275.J9 

UFCU1CI 3IME>tS:0*S 

••» v,' 2S!l.90t it' 

i»»j» v.* "1.351 it 

WOT IIM4TM ., • 1Z3O.309 . 



5 U = All 



^° T bl 



, 10 



.05 



.0 



.05 



.10 



1 1 { 


I 1 1 


I ; 1 


i 1 i 


i i ; 


t 1 I 


! I ! 


I i i 


w 














- 


-Ov^ 














- 


^ 


i — -e 








1 




— 


m 


f>- 












a 


! ! 1 


... .! 1 I 


I l i 


_, X _.1.-..1._. 


I. 1 i 


1 1 I 


1 

I ! 1 


i i i i 



0.2 0.H 0.6 0.3 1.0 

HEIGHT/SPAN 



1.2 



l.M 



1.5 




i„ h/b 

X. 1506.44 
:. 282.71 



HEIGHT/ 
S&AH 

h/b 




Angl« of Attack, 0! — Degr««s 






A -H.000 


, 0.0 


c H.000 


3.000 


1 12.000 


• 18.000 


G 20.000 


1 


ncrsm«n»a 


Pitching 


Moment 


Co«ffiei« 


int , ^Gn G 


5NO f'FfCT 


0.029 


0.08000 


0.05700 


0.03200 


0.01200 


-0.01500 


-0.05000 


-0.08000 


0.OSO ' 


0.05310 


. O^OO 


. 024 1 


0.00700 


-0.0210O 


-0.04920 


-0.06330 


0. 100 


. 03950 


. 02890 


0.01110 


-0. 00^00 


-0.02530 


-O.O'+OHO 


-0.05020 


0.200 


0.02 130 


0.01650 


0.00580 


-0.007MO 


-0.01390 


-0.01900 


-0.02800 


0.300 


0.01810 


0.01^60 


0.00590 


0.00130 


-0.00100 


-0.001 !0 


-0.00800 


0.300 


0.01 ISO 


0.00980 


0.00>»00 


0.00130 


0.00130 


0.00150 


-0.00160 


i.o ao 


0.00300 


0.00300 


0.30100 


0.0 


0.0 


0.0 


0.0 


1.500 


a.o 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



ENGINES* - , 
DATt */ 
HEV1SE0- 



■W 7? 



Figur. U. 1.1. 3-118 

GROUND EFFECT 



4.1.1.3-124 



* 



Rockwell International 

Spaca Division 



Landing Gear Down 



(ft 



*=■*. 



CONFIGURATION 

liSEUIC JIIITH «fWCU 

cinni a# ojakitt , i,*ii 1071.73 

o« 
*a*4M iimkmci 

HFUClCt .3t«MI0*$ 

iui w» '191301'.' 

1HH V»» T135I H 

,.< 31S5I- 
wot iiMart* \% • iiJIJO* • 



\\ 




0.6 0.8 1-0 

HEIGHT/SPAN 



Jl«J«r«NC* Pom* 




MIIGHTX 
/ffAN 

h/b 


Angle of Attack, a — Degrees 


. -H.00O 


• o-o 1 


c H.000 | 


g 3.000 


t 12.000 \f 18.000 | a 20.000 


Incrementa 


Pitching 


Moment Coefficient , A^GaNo «mjct 


0.025 


0.0HI30 


0.03330 


0.01860 


0.00930 


-0.01610 


-0.03610 


-0.06010 


0.030 ' 


0.03190 


0.02390 


0.01050 


. 00250 


-0.01 750 


-0.03610 


-0.05090 


0.10O 


0.01710 


O.OtO^O 


0.002HO 


-0 . 00690 


-0.0 1690 


-0.03530 


-a.c*030 


0.200 


0.02080 


0.01550 


0.00750 


-0.00050 


-0.00590 


-0.01520 


-0.01920 


0.300 


0.02590 


0.02190 


0.01920 


0.01650 


0.01650 


0.00990 


0.00990 


O.SOO 


0.00930 


0.00930 


O.OC800 


Q.00M30 


0.00>*00 


O.OO^OO 


O.OO^OO 


1.000 


o.oowoo 


0.00*00 


0.0 


0.0 


0.0 


0.0 


0.0 


l.SOO 


0.0 ( 0-3 


0.0 


0.0 


0.0 


0.0 


0.0 



MVI3fD< 



Figure 4.1.1. 3-119 I 

GROUND EFFECT) 



4.1.1.3-125 



D72-SH-CCCC IM 



cm -; 



«L* 



Rockwell International 

SpacaWviMon 




1X10 



1X10 



1X10 

PINF CPSID 



CONFIGURATION 
BASEL I Mi CRSITER VEHICLE: REFERENCE DIMENSIONS 

CENTER OF GRAVITY XO - FS 1076.7 [N. WING AREA SW - 2590.00 SQ.FT. 

OR YO - 8L 0.0 IN. UING SPAN SW » 79.055 FT. 

MGt€NT REFERENCE ZO - WL 375.0 IN. M.A.C. CW » 39.550 FT. 

BODY LENGTH L9 - 1590.3 IN. 



PINF (PSI) 


-*. IMP 

ff-lfa^a 


PITCHING M 


1.000E-07 


SH69.000 


1.000E-06 


9015.000 


1.000E-03 


8742.500 


3.000E-05 


7430.801 


1.000E-04 


4152.502 


3.000E-OH 


0.0 


4.S00E-OH 


0.0 


1.000E-03 


0.0 



rkrIki:rR FIGURE 4.1.1.3-120 

Pgi*J prTCHING MnMENT SURFACE IMPINGEMENT. DOWN-FIRING 



4.1.1.3-126 



D'Z-'CW-CCtL 1M 



* 



Rockwell International 
SpacaOivMon 



J- 



a 

01 



HO 



30 



ao 



10 



1 — I—r-TTTT 



08- 
1X10 



I ! I 1 I I 



"i 1 — TTTTTT 



1 1 — i.i ill 



-07 



1X10 



-06 



1X10 




"i i I i I 



I I i 



1X10 



-OH 



I ! I Ll'.j 



1X10 



-03 



PINF 


CPSI3 


CONFIGURATION 


BASELINE 0R81TER VEHICLE 


REFERENCE DIMENSIONS 


CENTER CF GRAVITY XO • FS 1076.7 IN. 


WING AREA SU - 2SS0.00 SQ.FT. 


OR YO « BL 0.0 IN. 


WING SPAN 8W - 78.056 FT. 


MCfCNT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW ■ 39.560 FT. 




9COY LENGTH LB - 1290.3 IN. 



PINF (PSII 


' 5M /3S.~-7^&r 


8,<0 


Js>° 


C€ PITCHING ^CMENT SI 


1.000E-07 


38.000 


0.0 


l.HOOE-05 


38.000 


a.o 


3.000E-05 


23.000 


0.0 


6.300E-05 


0.0 


0.0 


1.000E-OH 


0.0 


0.0 


t.OOCE-03 


0.0 


0.0 



ENGINEER 
OATE 1 



FIGURE 4.1.1.3--121 
ELEVCN PITCHING MOMENT SURFACE IMPINGEMENT. DOWN-FIRING 



i.1.1.3- 127 



'i* 



Rockwell International 

Space Divwon 



I 



150 



100- 



50 



en 



-60 



■100 



-150 
1X10 



= 



-07 



T I Mi! 



I I L ! 1..1.L 



1 1 — TTTTTT 




I I I i I 



i i i ] i i 




^7 



I I M ! 




i i ? i ! ! ri 



1X10 



■06 



IXIO' 05 

PINF CPSI3 



1X10 



-OH 



1X10 



-03 



CONFIGURATION 


BASELINE 0RBITER VEHICLE 


REFERENCE DIMENSIONS 


CENTER OF GRAVITY X0 - F5 1075.7 IN. 


WING AREA SW • 2S90.00 SQ.FT. 


OR YO - a. 0.0 IN. 


U1M3 SPAN SW » 73.056 FT. 


MCfCNT REFERENCE Z0-- W. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH L3 - 1290.3 IN. 



PINF (PSII 


■ a *^8w* 


ft lb 


n-'deq 


5w<0 


«**o - 


D8F PITCHIN 


G FOMENT S 


1.000E-07 


75.000 


-75.000 


1.000E-06 


75.000 


-75.000 


1 .000E-O5 


98.000 


-98.000 


2.50CE-05 


72.000 


-72. COO 


4.500E-05 


115.000 


-115.000 


7.Q0CE-05 


115.000 


-115.000 


1 .800E-04 


0.0 


0.0 


H.500E-OH 


0.3 


0.0 


I.000E-03 


0.0 


0.0 



ENGINEER_ 
OATE Z 



FIGURE 4.1.1.3-122 

BODYFLAP PITCHING MOMENT SURFACE [MP INGEMENT, ON-PIPING 



4.1.1.3-128 



tD 7 2 - S i ! -COCC hVl 



€> 



Rockwell International 
Space OMston 



J/0 INF 
.] 

> l I I 



.2 



a 

i 




15 



20 



30 35 

ALPHA CDEG3 



40 



50 





AL^HA CLtU) 




" 17.500 


ea.auu 


27.311U 


32.300 


su ■ /so 


OJ/OINF 


A, 


3 


c 





E 




MfltMNG hCf-LNT j 


J.W, , 




— oio — 


O.U 


0.0 


0.0 


0.0 


O.U 


. 0050 


o . 00495 


0.00300 


. 0C563 


. 00544 


0.00518 


0.0100 


. 00S52 


. 0070S 


0.01021 


. 009S6 


0.00955 


. 02CO 


0.01509 


0.01452 


0.01853 


0.01830 


0.01756 


. 0300 


0.02091 


0.02130 


0.026C5 


0.02574 


0.02494 


. 0400 


0.02599 


0.02712 


0.03249 


0.33228 


0.03138 


. 0500 


0.03032 


. 03207 


0.03792 


. 03790 


0.03697 


0.0600 


0.03391 


0.026S8 


. 04237 


0.04262 


0.C4174 


0.0700 


0.03575 


0.03942 


. 04582 


. 04642 


. 04553 


. 0800 


0.03885 


0.04180 


0.04827 


. 04932 


. 04874 


. 0900 


0.04020 


. 04333 


0.04973 


0.05132 


. 05099 


g. tooo 

. 1 1 00 


. 04080 
. 04080 


0.04400 
0.04400 


0.05020 
. 05020 


0.05240 
0.052S0 


. 05240 
. 05297 


0.12C0 


0.04080 


0.04400 


. 05020 


. 052S0 


. 05270 


0.1300 


0.04080 


0.04400 


. 05020 


0.05550 


. 05270 


0. !<*00 


. 04080 


0.04*00 


Q. 05020 


0.05250 


. 05270 



£=(i*J(Tt)"- ai513 (i) 



riijSmai* Flow rat* 

VjS txil velocity 

n s nufflbtr of thruilcrs 



A,.,= Iff* 
S,.,= 2690 M 



ACm 



J I 



= A + A, 



Interpolate for a'l not 
shown a^Sti calculation 
of given a'l only. 



flJHA.J 



m 



22.500 
27.500 
32.500 
39-750 



A 



k 1 



u.uoiy 

-0.0013 

0.0008 
0.0007 
. 0006 



TT7B5D- 
0.3820 
0.9910 
0.9710 

0.S370 



ET3HIE3SSHOPZ 



<^UI, M (V^l.x 



-a. /sua 
► .2900 
K9700 
t.5400 



IT 

"•9 
0.0 
0.0 

JUL 



0.0050 

0.0050 
0.0050 
0-00=0 



0.1O0O 
0.1000 
0.1000 
0.1050 

0.1200 ! 



ENGIrCER hr 9 
DATE 1U£l3!?\ 



FIGURE 4. 1.1. 3- 123 

PITCHING MOMENT JET INTERACTION. DOWN-FIRING 



4.1.1.3- 12? 



*1* 



Rockwell International 

Space Division 



MJ/MINF 
.05 



AC„ 



<ii 



.03 



.02 



.01 









5 "^d IS 20. 25 30 35 HO 



20 . 25 30 

££ - CDEG] 



45 



50 









CC 


( CSC- i 








7.500 


12.500 


17.500 


22 . 500 


27.500 , 


32.500 


33. /=0 


MJ/MthS" A 


A 


3 


C 





E 


r 


G 






PITCH! 


k C .iCI-iNT J 


1 ,SF 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


o.ooi 


0.0 


0.00053 


0.0007S 


0.00! 10 


0.00150 


0.00150 


0.001S0 


0.005 


0.0 


0.00314 


0.00379 


O.OC420 


0.00415 


0.C0343 


0.00310 


0.010 


0.0 


. 00235 


0.00508 


0.00647 


. 00675 


0.00571 


. 0C4g4 


0.015 


0.0 


0.002S5 


0.CCS2S 


0.00851 


. 009C3 


o.ccsca 


. 00676 


0.020 


0.0 


. 0C2B4 


0.0O734 


0.01032 


0.01 115 


. 1 046 


0.00879 


0.025 


0.0 


0.00229 


0.00831 


0.01189 


0.01297 


0.01279 


0.C1CS5 


0.030 


0.0 


0.00303 


0.00917 


0.01323 


0.01452 


0.31500 


0.C1259 


0.035 


0.0 


0.0032H 


0.00SS3 


0.01433 


0.01531 


0.01701 


0.01 u 64 


0.040 


0.0 


0.00353 


0.01058 


0.01520 


0.01634 


0. GISTS 


0.01652 


0.045 


0.0 


0.00390 


0.01113 


0.01584 


0.01761 


0.02018 


0.01317 


0.050 


0.0 


0.00435 


0.01158 


0.01625 


0.01813 


0.02119 


0.0IS42 


0.055 


0.0 


0.00487 


0.01191 


0.01S42 


0.01837 


0.02173 


0.02031 


O.OSO 


0.0 


0.0C549 


0.01214 


0.01S3S 


0.01837 


0.02173 


. 02077 


0.0S5 


0.0 


0.00549 


0.01214 


0.0153S 


0.01837 


0.02173 


. 02077 


0.070 


1 0.0 


. 005^8 


0.31214 


0.01535 


0.01837 


0.02173 


0.02077 



Vj s »jsit velocity — fp» 

v a s fr»«rr«<im velocity ~fpJ 

d t s nozzle hoif angle at exit 



1C„ 



= A + A 1 &)^ 2 (^A 3 (-%) : 



ALPHA (CEO) 


AQ03.KIN,rtAX 


A 1 


A, 


A 2 


A 3 t-'AA.J 




PITCHIM3 MCfCNT JI.SF 


7.500 


0.0 


0.0 


0.0 


0.0 


0.00500 


. 06000 


12.500 


O.0O34O 


-0.053*0 


1.56690 


0.0 


0.00500 


0.06000 


17.500 


0.00240 


0.29900 


-2.11000 


0.0 


0.00500 


0.06000 


22.500 


0.00170 


0.52400 


-4.650C0 


0.0 


0.00500 


0.06000 


27.500 


0.00130 


0.59700 


-5.210OO 


0.0 


0.00500 


0. 05500 


32.500 


0.00130 


0.40500 


4.52000 


-93.30000 


a. 00500 


0. 05500 


38.750 


_p. 00160 


0.27100 


5 . 22000 


-90.20000 


0.00500 


0.06000 



Kj, -'.0 
Interpolate for a's noi 
shown aS/e* calculation, 
of given a's only 



CAUTICN: Polynomial curve-fit, is valid CNLT for the aass flow ratio range 
eiven in the above table. 



ENGINEER " 



-n*-,,*™ „ FIGURE 4.'.1.3-12<Y 

Sre^fTSEB P I TCH I NG MCWENT . U I NTHRACT I CN . S ICCrEIgWG.. 

L. 1.1. 3-130 



j::'-ccco im 



* 



Rockwell International 

Space Ohmion 







-.006 





— A.PHA (CtGI 




17.300 


<SS.=00 


27.500 


32.300 


sa. rsu 


OJ/OtNF 


A 


8 


C 





5 




PTiCWI 


37-HCf-CNT „ 


l.JF 




w o.o — 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0050 


-0.00165 


-0. 00004 


0.0 


0.0 


-0.00030 


0.0100 


-0.00219 


-0.00OC8 


0.0 


0.0 


-0 . 00058 


0.0150 


-0.00258 


-0.00012 


0.0 


0.0 


-0 . 00085 


0.0200 


-0.00313 


-0. 00034 


0.0 


0.0 


-0.001 10 


0.0300 


-0.00394 


-0 . 00095 


0.0 


0.0 


-0.00157 


o.ohoo 


-0.00460 


-0.00171 


0.0 


0.0 


-0.00198 


0.0500 


-0.00511 


-0.00249 


0.0 


0.0 


-0 . 0C233 


0.0600 


-0.00549 


-0.00319 


0.0 


0.0 


-0 . k C02S2 


0.0700 


-0.00572 


-0.00370 


0.0 


0.0 


-0 . 00285 


0.0800 


-0. 0058 1 


-0 . 003S8 


0.0 


0.0 


-0 . 00303 


0.09O0 


-0.00576 


-0.00388 


0.0 


0.0 


-0.00315 


a. iooo 

0.1100 


-0.00575 


-0.00388 


0.0 


0.0 


-0.00321 


-0.0057S 


-0.00388 


0.0 


0.0 


-0.00321 


0.1200 


-0.00576 


-0.00388 


0.0 


0.0 


-0.00321 


0.1300 


-0 . 00576 


-0 . 00338 
1 -0.C0388 


0.0 


0.0 


-0.00321 


0.1400 


-0. 00576 


n.o 


0.0 


-0.0032! 



±°mj(t£>--™^t) 



m^ mass flow rat* 

VjS «xit velocity 

n = number of thrusters 



A,.,= lft* 
S r .,r 2690 ft 2 



AC„ 



s A n +A, 



MJSOl 



nl 1 

22.500 
27.500 
32.E00 

38.750 



A 



M 



-0.0011 

o.o 

0.0 
0.0 

_JLJ2 



-fl.1160 
0.024H 
0.0 
0.0 

-0.0610 



?B 



ymajiNti ,A>tNf jLUi 



<v*.l n <*#-U 



o:;M 

-2.44O0 
0.0 
0.0 

_lJ32g_ 



ir 



19.1000 
0.0 
0.0 . 

g.g 



■0.0050 
0.0150 
0.0050 
0.0050 

o.ooso 



o.oaoo 

0.0800 
0.1200 
0.1200 

o. iooo l 



*>(£)->(£•; 



Interpolate for a'% not 
shown ayY«« calculation 
of given Ot's only. 



ENGll^£ER 

OATE " 



FIGURE 4.1.1.3-125 
PITCHING MOMENT JET I NTERACTICN. UP-FIRING 



4-1.1.3-131 



M 



* 



Rockwell International 

Space Division 

L_ 



OE REF CDEG3 



= -30.000 



.0 






.005 



-.010 



-.015 



OJ/OINF 
.1 .2 

rn — i — i — ; — j — i — i — i — i — | 

<•■■■■ ■ ■' i i i — 




30 35 

ALPHA CDEGD 



oj/oiy 



0.0050 

o.oioo 
o . oaoo 

0.0300 
0.0400 
0.0500 
0.0600 
0.0700 
0.0800 
0.0900 
0.1000 
0.1 100 
0.1200 
0.1300 
0.1400 



17:500' 

A 



no 

-0.00091 
-0.00172 
-0.00302 
-0.00383 
-0.00434 
-0.00437 
-0.00397 
-0. 00315 
-0.00190 
-0.00023 
-0 . 00023 
-0.00023 
-0.00023 
-0.00023 
-0.00023 



^=(i?J(t:)" i0 ' I5i3( t) 



m,s mait f l_o*» reie 

VjS-txit velocity 

n s. number of rhrvnterj 



A,*= lFt 2 
S r ,,= 2690fr z 



-22~=DTr 



^AJfey' 



^ 



-o 



0.00134 
0.00258 
00476 
-0 . 00654 
-0.00792 
-0.00890 
-0 . 00948 
-0.009S5 
-0 . 00944 
-0.00882 
-0.00832 
-0.00882 
-O.0C882 
-0.30632 
-0 . 0C832 



^73 
IMS HCr-LMI 



to 

-0.00215 
-0.00413 
-0.00746 
-0 . 00993 
-0.01170 
-0.01263 
-0.01274 
-0.01206 
-0.01058 
-0.00829 
-0.00829 
-0 . 00829 
-0.00829 
-0.00829 
-0.Q0S29 



32.300 
D 

ji.cr 



33.750 
__£ 



-0.00172 
-0.00331 
-0.00511 
-0 . 0084O 
-0.01019 
-0.01148 
-0.01225 
-0.01252 
-0.01229 
-0.01155 
-0.01155 
-0.01155 
-0.01155 
-0.01155 
-0.01155 



-0.00133 
-0.00261 
-0.C049S 
-0.00707 
-0 . 008S4 
-0.C1055 
-0.01192 
-0.01303 
-0.01390 
-0.01453 
-0.01453 
-0.01453 
-0.01453 
-0.01453 
-0.01453 I 



mi* 



• **. &)■ 



ALWA (DEO) 

22.500 
27.500 
32.500 
39-750 



Ao 



■mar 
o.o 
o.o 
o.o 

JLJL 



ML 
-'0'. 1535 s * 
-0.2780 
-0.4530 
-0.3560 
-0.5730. 



uim,im HJjM=.yi JI.J-' 



'3.1200 
2.0000 
4.0100 
2.5300 

... 1.240Q 



? 



|(V*JJ(V*Jm, 



TJ.- 
0.0 
0.0 
0.0 
JLfl 



■a. 0050 

0.0050 
0.0050 
0.0050 
0.0050 



"3. 0500 
0.0900 
0.09OO 
0.0900 
Q.0900 



Interpolate for <s'» net 
shown off** calculation 
of given &'» only. 



ENGlhCEH 

DATE 



FIGURE 4. 1. 1.3-126 

Fl FVflN PITCHING MCMENT JET INTERACT! CN. GOWN-FIRING 



4.1.1.3-132 



£:" 7 2 -S'i- cCtC !:V1 



#1% 



Rockwell International 

Sp e cs OMrton 

L 



DE REF CDEG) 



10.000 



~3 

Id 

2: 



.020 



.015 



.010 



.005 




.0 



15 



aZ "">~ 7 ^ ^ r www 

A^^ ~-w / ^~ n \\ ww w 

20 25 30 



i r 



0J/0INF 



30 

ALPHA 



35 
CDEG] 



i''l 



I l l I 



j__j 



40 



45 



50 



CXI/CUM:' 


1 ALHHA lUtG) 


17.500 
A 


22.300 
B 


27.500 

c 


32.300 
D 


38. /5J 




ISVIHWNU Mit.NI 


vM A l* 


1 II 


J.O 


0.0 


O.U 


0.0 


0.0 


0.0 


. 0050 


0.00025 


0.0 


0.0 


0.0 


0.0 


0.0100 


. 00059 


0.0 


0.0 


0.0 


0.0 


0.0200 


0.00154 


0.0 


0.0 


0.0 


0.0 


0.0300 


0.00285 


0.0 


0.0 


0.0 


0.0 


0.0400 


0.00452 


Q. 00129 


0.0 


0.0 


0.0 


0.0500 


0.00655 


. 00327 


0.0 


0.0 


0.0 


0.0600 


0.00894 


. 00593 


0.0 


0.0 


0.0 


0.0700 


0.01169 


0.00925 


0.0 


0.0 


o.a-- 


0.0800 


0.01480 


0.01323 


0.0 


0.0 


0.0 


0.0900 


0.01755 


0.01630 


0.0 


0.0 


0.0 


0.1000 


0.01755 


0.01690 


0.0 


0.0 


0.0 


0.1100 


0.01755 


0.01690 


0.0 


0.0 


0.0 


0.1200 


0.01755 


0.01630 


0.0 


0.0 


0.0 


0.1300 


0.01755 


0.01690 


0.0 


0.0 


0.0 


0.1400 


0.01755 


0.01690 


o.o 


0.0 


0.0 



%--&jjty--™ i <t) 



iftj= mats Mow rote • 

VjS exit velocity 

n — numb«r of thrusters. 



A r# ,= 1ft* 
S,.,= 2690fr 2 



<*, 



<*, 



•«7 



iVHft, .<E5fi> 



W 



22.500 
27.500 
32.500 
3SLJ5SL 



A 



<\ 



o.o 

0.0 
0.0 

JLIL 



ffi 



-0.1010 
0.0 
0.0 
0.0 



^ 



..-JO" 
3.3300 
0.0 
0.0 

SL2 



Hssrgnz 



iMuXj^A-U' 



0.0 
0.0 
0.0 
JLS 



u.oosir 

0.0300 
0.0050 

0.0050 
0-0050 



0.0880 
0.1000 
0.1000 

JLiflOJL 



Interpolate For a's not 
shown a//** calculation 
erf given a's only. 



0ATE__._^JIa(.2_S. 



FIGURE 4.1.1.3-127 

ELEVCN PITCHING MOMENT JET INTERACTION. DOWN-FIRING 



U. 1.1. 3-133 



SD72-SH-CCCO IM 



0$ 



Rockwell International 
Space Division 




C<j CDEG3 









o«- ic 


i'3) 








7.500) 


12.500 


17.500 I 


22.500 


27.500 


32.500 


-.3 . 750 


MJ/MINF A 


A 


3 


C 1 





r 


r 









C£ PITCH! NO r-C'-oNT 


Jl .Sr 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.001 


-0.00013 


0.00005 


0.0 


-0.00020 


-0.C0C23 


-0.00015 


0.3C0GS 


0.005 


-0 . 0OOS5 


0.00027 


0.0 


-0.00101 


-0.00114 


-0 . 00073 


0.C0025 


0.010 


-0.00121 


0.00C57 


. 0.0 


-0.00186 


-0 . 00209 


-0.C0I77 


0.CC0C9 


0.015 


-0.00166 


0.Q00S0 


0.0 


-0.002=5 


-0 . 00594 


-O.0C2S4 


-0.00C4" 


0.020 


-0.00200 


0.C0I26 


0.0 


-O.00309 


-0.C0339 


-0.3G42! 


-0.00127 


0.025 


-0. 00223 


0.00165 


0.0 


-0.00346 


-0.00375 


-0.00552 


-0.00233 


0.030 


-0 . 00236 


0.00207 


0.0 


-O.0OZ63 


-0.00291 


-0.00S73 


-0 . 00356 


0.035 


-0.00237 


0.00252 


0.0 


-0 . 00374 


-0 . 00392 


-0 . 00793 


-O.0C437 


0.040 


-0.00237 


0.00301 


0.0 


-0.00374 


-0.003S2 


-0.0C591 


-O.0C621 


0.045 


-0.00237 


0.00352 


0.0 


-0 . 00374 


-0.00392 


-O.0C953 


-0. 0075 1 


0.050 


-0.00237 


0.00406 


0.0 


-0.0037*+ 


-0.00392 


-0.01004 


-0.CCS70 


0.055 


-0.00237 


0.CC405 


0.0 


-0.00374 


-0.00392 


-o . o : co4 


-0 . GC870 


0.060 


-0.00237 


0.00406 


0.0 


-0. 00374 


-0.00392 


-0.01CC4 


-0 . 00970 


0.065 


-0.00237 


0.00406 


o-.o 


-0.00374 


-0.00392 


-0.01004 


-0 . OC970 


0.070 


-0.00237 


0.004C6 


| 0.0 


-0.30374 


-0 . 003=2 


-0.01 CC4 


-0 . 0CS7O 



vj r «xir v«to«ify -• Fpi 

v,, s fr»#jrr»am v«iocity— fps 

9) = noizU hoif angi« at «xit 



4C fl 



^' ■*.**.(*:)**.&)**.&) 1 



ALPHA (CEO 


Atttt. Mr N.MAX 


- X =1.0 


A 


A,_ 


A 2 


A 3 | 


' J /Ovmn|( 'AmX*** 


A„ i.u 




ce 


PITCHING MOMENT Jl.Sf 




Interpolate 


7.500 


0.0 


-0. 14290 


2.14620 


• 0.0 


0.GG5C3 


0.03530 


sho*n a/fa I 


12.500 


0.0 


0.05090 


0.605SO 


0.0 


0.0020O 


0.05000 


17.500 


o.a 


0.0 


0.0 


0.0 


0.00500 


o.osaco 




22.500 


0.0 


-0.21800 


3. 18000 


0.0 


0.005C3 


0.03420 




27.500 


0.0 


-0.24800 


3.92000 


0.0 


o.oosoa 


O.03I6O 




32.500 


0.0 


-0. 12400 


-6.20000 


93.30000 


0.005C3 


0.05000 




38.750 


q.o 


0.1 0000 


-9.99000 


90.20000 


. CC50C 


. 05000 





For a 5 not 
calculation, 
only 



CAUTICN: Polynomial, curve-fit is valid CTLT for the oass flow ratio range 
given in the above table. 

r^ih£E9 fP FIGURE 4.1.1.3-128 

oS-Stfe". ELEVCN PITCHING MC^ENT JET ;NTC3ACTICN.SICEj£IRING 



X^7 



k. 1.1.3-13: 



D 



H-CC'-C 1M 



€> 



Rockwell International 

Space Division 



>e w CDEG3 

.013 



MJ/MINF 
.05 



.010 



AC, 



m, 



<j. 



.005 



( I \ 



TT 



I i l T 



till 






— >- ■ —— — ~^-** • 



i-J-L-L 



I^^P^fe^K^l^^S^^ 



'ill 



20 25 

06 CDEGD 



30 



40 



45 



.10 



1 ' ' t 









oo iceo) 


~ 






7.500 


12.500 


17.500 


22.500 


27.500 


32.500 


38.750 


MJ/MIKF A 


A 


3 


c 


D 


e 


F 


G 






C£ PITCHING MC.-SNT 


Jt.SF 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


o.oni 


0.0C029 


0.00038 


0.00023 


0.00007 


0.0 


0.00027 


0.00019 


0.005 


0.00142 


0.001SO 


0.C01I6 


0.00034 


0.0 


0.00137 


0.00095 


0.010 


0.00250 


0.00344 


0.00229 


0.00077 


o.oooot 


0.00242 


0.00159 


0.015 


0.00355 


o.oo^gi 


0.00340 


0.00127 


0.00001 


0.00322 


0.0C20I 


0.020 


0.00429 


0.00621 


0.004H9 


o.ooies 


. 000C2 


0.00333 


0.002=5 


0.025 


0.00477 


Q.0073S 


0.00555 


0.00254 


0.00049 


0.00433 


0.00240 


0.030 


0.00503 


0.00933 


0.00658 


0.00329 


0.00115 


0.00479 


0.00252 


0.035 


0.00507 


0.00914 


0.00760 


0.0C413 


0.C0199 


0.00529 


0.00252 


0.040 


0.00507 


0.00979 


0.CCS53 


0.00506 


0.00302 


0.00587 


0.00252 


0.045 


0.00507 


0.01027 


0.00955 


0.006C6 


0.C042H 


0.00652 


0.00252 


0.050 


0.00507 


0.01059 


0.01049 


0.00715 


0.005S4 


0.00761 


0.00252 


0.055 


0.00507 


0.01059 


0.01049 


0.00715 


f 0.00564 


0.00761 


0.00252 


0.060 


0.00507 


0.01059 


0.01049 


0.00715 


0.00554 


0.00751 


0.00252. 


0.065 


0.00507 


0.01059 


0.01C49 


0.00715 


0.00564 


0.00761 


0.00252 


0.070 


1 . 00507 


0.01059 


0.01049 


0.00715 


0.00554 


0.00751 


0.00252 



v. 5 exit velocity ~ fp* 

v M ~ fre«*»reani velocity -- fpt 

9 } s. nozzle half angie at exit 



AC«, 



22JU 



SA o + A i(TT) + A a(Tfc) I+A 3&) J 



ALPHA <CEG> 






A0O3.M!N.f<AX 




Ag 


A, 


A 2 


A 3 


<*yft-UT'A.U 




T ce 


PITCHING ,-Cf€NT Jl.Sr 




'""7.500 


0.0 


0.30640 


-4.62700 


0.0 


0.00500 


0. 0331 O 


12.500 


0.0 


0.37660 


-3.29520 


0.0 


0.0C500 


. 05000 


17.500 


0.0 


0.23400 


-0.46500 


0.0 


0.00500 


0.05000 


22.500 


0.0 


0.06000 


1. 55000 


0.0 


O.CG500 


. 05000 


27.500 


0.3 


-0.07360 


3.73000 


0.0 


0.02000 


0.05000 


32.500 


0.0 


0.31100 


-7.e4000 


93.30000 


0.00500 


. 05000 


38.750 


0.0 


0.22400 


-7.J7000 


SO. 20000 


. C0500 


0.03000 



K Jt - I-© 



\H 



Interpolate for a j not 
shown affai calculation, 
of given ac'» only 



CAUTICN: Polynomial curve-fit i3 valid CNLI for the aass flow ratio range 
given in the above table . 



ENGINEER 
OATE 



"3& 



FIGURE 4.1.1 
TL ELEVCN PITCHING MC^FNT 



.3-129 

JET INTERACTION. SICE -FIR IMG 



t.l.l.j-135 



SD72 



S 



;-!■ ccec im 



'1* 



Rockwell International 

Space Division 

L_ 



GJ/OINF 



DBF REFCDEG3 



= -14.250 



a 

Li. 



.015 



.010 



.005 



.0 











A 


:wa (cmi 






" 17.3CI0" 


22.5UU | 


<tl . bOO 


.52.300 


iB . /=U 


OJ/OTM r 


A 


8 


c 





E 




CSF PIlCWNU MUMtNl 


^tPls 




— a 


■"D.a 


0.0 


a. a 


0.0 


0.0 


. 0050 


. 00069 


. 00040 


0.00006 


0.0001! 


0.00042 


0.0100 


. 00 1 35 


0.00073 


0.00018 


0.00029 


. 00CS6 


. 0200 


0.00=56 


0.00 146 


0.C0C5H 


0.00032 


0.0C18H 


0.0300 


. 00390 


0.00203 


0.00110 


0.00159 


. 00294 


0.0400 


0.00503 


. 00250 


0. 00184 


0.002S0 


0.00416 


. C500 


. 00620 


0.00296 


0.00277 


. 00384 


. 00549 


. 0600 


. 0C72S 


0.00311 


. 00390 


. 00533 


0.0CS95 


0.0700 


. 00826 


0.00325 


0.00521 


. 00706 


. 00852 


0.0800 


. OOS20 


0.00331 


0.00671 


. 00903 


. 1 02 I 


0.0900 


0.00991 


0.00327 


. 00805 


0.01078 


0.01 165 


0. 1000 


0.00S91 


0.00327 


. 00805 


0.01078 


. 1 1 65 


. 1 1 00 


0.00991 


0.00327 


0.0C805 


0.01078 


0.01 i65 


0.1200 


0.00991 


. 00327 


0.00805 


0.01073 


0.01 165 


0.1300 


0.00931 


. 00327 


. 00805 


0.01073 


0.01 165 


0. 1^00 


0.0099! 


0.00327 


0.00805 


1 078 


0.01165 



(4 



A r . ( yus 



/^sLj„= 0.1543 



(t) 



m,= mass flow rata 

v,= exit velocity 

n s number of tnrusterj 



K,,- 1 f» 2 
S,„=2690ft 2 



^.^♦*. (■&**.&)'-.&/ 



ALPHA r 



T7r=ur 

22.500 
27.500 
32.500 
3BJ5Q,. 



A 



o.o 
o.o 
o.o 

JUL 



TJ7T3 1 — 
0.0835 
0.CC81 
0.0169 

JL5S22 



isF^ 



TZ 



-0.5270 
0.9470 
1 .2000 
0-5530 1 



^CtfMUl. 



mx» m .u 



U7T 

0.0 

0.0 

0.0 

<L_0_ 



0.0050 
0.0050 
0.0050 
0.C050 

0.00=0 



o.oyyu 

0.0880 
•0.0880 
0.0880 
O.OS80 



interpolate for Ct'i not 
shown aS/*i calculation 
of given a's only. 



DATE IZJi„l- 



FIGURE 4.1.1.3-130 ,-,„„„* 

SCQYFLAP-P ITCHING MOMENT JET INTERACTION. DOWN-FIRING 



4.1.1.3-136 



C T 



iM 



L 



,Kr 



J(%J 



o 
u 

ST 

a 



cr Cm, 



Rockweil International 

Space Division 





i 1 ; 


1 i 1 


i 1 1 


i 1 i 


. ; r 


: 1 ] 


1 1 1 


1 i . 


" i W 


1 ! ! 


1 i 1 


"T i T - 




- 






















- 




- 






















- 


.3 


- 






















- 


- 






















_ 




- 






















- 




- 






















- 


























- 


.a 
















































- 




- 






















- 




- 






















- 


























- 


.0 


"1 - 1 


,L,1 1 


I Li. 


..: . 1 .. l. 


! 1 1 


1 1 J 


! 1 i 


1 1 1 


_1_L_L 


1 ' 1 


: i 1 


J I I 



16 IS 20 22 2H 26 28 30 

ALPHA CDEG3 



3H 



36 



33 



40 



CO^IGURATICN 


BASELINE CRBITER VEHICLE 


REFERENCE OlrCNSIONS 


CENTER CF GRAVITY X0 - FS iOTS.7 IN. 


U[NG AREA SU ' 2590.00 SQ.FT. 


OR YO - SL 0.0 IN. 


WING SPAN 9W « 78.056 FT. 


MOrtNT REFERENCE Z0 - UL 375.0 IN. 


M.A.C. CW » 39.550 FT. 




BCCY LENGTH LB » 1290.3 IN. 



ff(Oj/'6») 



= if down 



1 ring jgt group ij 



inoperative on one side. 



ALPHA (DEG) 


dCm,, 


<J(«*j/<aJ 


PITCHING 1 


17.500 


. 37000 


22.500 


. 32000 


27.500 


. 30000 


32.500 


0.31000 


38.750 


0.33000 



0<(-^)<0.03 




ENGIhCERT^-D FIGURE 4.1.1.3-131 

0*TZ-3u~jJsiL5? PITCHING MOMENT JET INTERACT I CN CARRYOVER. CIOWN-P I R IN 3 



4.1.1.3-137 



■:i CC . C IM 



0^ 



Rockwell International 

Space Division 



4. 1.1. 4 TRIM AND STABILITY. This section presents the trim and stability 

characteristics of the Orbiter Vehicle (0V102) in a manner considered 
useful for determining the longitudinal trim and stability limits. 

Trim and stability limits are presented for the speed brake and body 
flap control schedules given on Figure 4.1.1.14-1 (b & c) for both 
forward (0.65 L B ) and aft (0.675 L 8 ) design centers-of-gravi ty. The 
control schedules presented on this figure are for determining maxi- 
mum obtainable trim limits and do not reflect actual flight control 
system schedules. A reserve for maneuvering, trimming spanwise center 
of gravity offset (AY CG ) , manufacturing misalignments, and aerodynamic 
uncertainties has been applied to the limits of the elevon effective- 
ness data to establish the limits shown on Figures 4.1.1.4-2 through 
4.1.1.4-11. 

For a positive elevon deflection, the aforementioned reserve is equiva- 
lent to five-degrees of elevon. Therefore, aft center of gravity trim 
limits are based on a positive elevon deflection of 15-degrees for 
Mach numbers less than or equal to 10. A positive elevon deflection 
of 10-degrees was used for Mach numbers greater than 10 due to thermal 
protection system design limits during maximum heating conditions. 
Forward center-of-gravi ty trim limits are based on an incremental 
pitching moment coefficient reserve of 0.015 for Mach numbers less 
than or equal to 10 and 0.020 for Mach numbers greater than 10. The 
longitudinal trim limits are presented as functions of angle of attack. 
For a summary of these trim limits see Section 2.2. Thfs summary has 
been presented for the TPS design trajectory (14414.1) angle of attack 
schedule shown on Figure 4. 1 . 1 .4-1 (a) . 



4 .1 .1 .4- ! 

SD72-SH-0060-1M 



'i* 



Rockwell International 

Space Division 







: r"^^F^.L^3 



8 12 16 

Mach Number , M 



20 



24 



ITS OOWNI 30 




100 



30 



Speed Brake 
Deflection, 60 

i" 

Degrees *° 

20 



* 6 

Mach Number , M 



4 6 

Mach Number , M 



10 




A 




*» 



[Stl ALSO 1 



Figure 4.1. 1.4-1 

CONTROL SCHEDULES 



4.1.1.4-2 



SD72-SH-0060-1M 



0$& Rockwell International 

Space Division 




.64 .68 

Center of Gravity, Xg 9 




Degree} q 



Center of Grcvity cg 

Li 



V*s£> i-Z-W 



Figure 4.1.1.4-2 

STATIC TRIM CAPAB! 



LITY I 



= 25 



8 S . 

Sct>*dul« 



a T „ =10 



4.1.1.4-3 



SD72-SH-0060-1M 



#1* 



Rockwell International 

Space Division 



Degrees q 





^ = 25 

Schadgl* 

a TP5 = IC 

Otjign 
r rof acfory 



S9 =2^ 

ScH«dul« 

= 10 

•TPS 
Oaiign 
Trai.eio'y 



Angle 

of 20 

A'ttock, 
a 

Degrees q g 



-20 



.56 



.60 



.64 



.68 .72 

Y 

Center of Gravity c ? 

u 



.76 



V&=H±± 



Figure 4.1.1.4-3 1 

STATIC TRIM CAPABILITY j 



~K^S 



4. 1.1. 4~- 



SD72-SH-0060-1M 



Rockwell International 

Space Division 



Angle 

of 20 

Attack, 
a 

Degrees q 




Center of Groviiv, * c 9 




Degrees q 



.56 



.60 .64 .63 

Center of Gravity , 



.72 



Li 



\~x£Lhzk2l. 



Figure 4.1.1.i*-i. 



STATIC TRIM CAPABILITY 



8« = 25 ' 

Schtdul* 

a =10° 



.1.1.4-5 



SD72-SH-0Q60-1M 



$B 



Rockwell International 

Space Division 





5 S8 =25 

Sth.duL 

a Tfi =10 

r f o|«<fory 



Center of Gravity ; r A «g 



60 is 




.56 



.60 



.64 .68 

Center of Gravity ( 






>*i£ W-^? 



Figure I,.. 1.1. 4-5 

STATIC TRIM CAPABI 



LITY1 



S« = 


25 


SchWul. 




«T ?5 = 


10 


0«ngn 




Tfaj^'tro 


r 



4.1.1.4-c 



SD72-SH-0060-1M 



Ipl^ Rockwell International 

Space Oivtsjon 




Degree* q ===^= ^ _ ' [-S^Z^T~—. ^ L;"~ Z ^ 



Center of Gravity ; J^£9 
I, 




Degrees q ---j---— -■- 



Center of Gravity cg . 



V£>Q 6-6-7^ 



Figure 4.1.1.4-6 

STATIC TRIM CAPABILITY 



u = 55 






= 10 



4. 1.1. 4-' 



SD72-SH-0060-1M 




Rockwell International 

Space Division 




D*gr««j q -p- 



Center of Grovity n , c 9 



Figure 4.1.1.1^-7 

STATIC TRIM CAPABILITY 



V3^ *-6-7«> 



.1.1. a-a 



SD72-SH-0060-1M 



Sl^ Rockwell International 

Space Division 





Degreej q 



.56 



.60 .64 .68 .72 .76 

Cenrer of Gravity ; *<=9 




Degrees q -—■■ — ^— i— 



5 S , =55 

= 10 



a 



.56 



.60 



.64 .68 

Center of Gravity f 



L. 



.72 



KZ>$h 6-6-73 



Figure i+.l.l.i+-o 

STATIC TRIM CAPABILITY 




'Tr«i*<l«ry 



S» = 55 

«TP3 = 10 
Trajectory 



4.1.1.4-9 



SD72-SH-0060-1M 



Rockwell International 

Space Divtsion 




V.2££> 6-6-7? 



t.l.l.i-10 



SD72-SH-0060-1M 



Rockwell International 

Space Division 




\262> 6-6-79 



Figure 4.1.1.4-10 I 

STATIC TRIM CAPAB ILITY j 



4.1.1.4-11 



SD72-SH-0060-1M 



Rockwell International 
Space Division 



5„ =^.2 




.60 .64 .68 -72 

Center of Grovity, * c 9 



kii^=£EE^^ S„ =S^.2 




Degrees q. ^^~^^rff^ 



sa 

St h .Jul. 
Trejt«<l«py 



.56 



.60 



.64 .63 .72 

Center of Gravity f cg 



.76 



V3Xi> £-6-7^ 



Figure 4 . 1 • 1 • 4-11 

STATIC TRIM CAPABILITY 



_J 



4.1.1.1.-12 



SD72-SH-0060-1M 



C^K.3 Rockwell International 



t%> 



Space Division 





Degreej q 



.56 

60i=e 



.60 .64 .68 

Center of Gravity f * c 9 







.56 



.64 .68 

Center of Gravity } 






Figure I4.I.I.L.-I2 



\£QJdz¥L-2 



STATIC TRIM CAPABILITY 



tPTfi'i^ 



8$i =97.2 

Sch.J u l. 



SI 



= 



5<n«dwl« 




«T- 5 


H 


3«li«n 




Trajectory 




30.5° 


1C 


31.0° 


15 


36.0° 


20 



4.1.1.4-13 



SD72-SH-0060-1M 



€* 



Rockwell Intematior.o- 

Space Division 



4.1.2 STABILITY-AXIS DATA. The longitudinal aerodynamic characteristics in 
the stability-axis system are: 

4.1 .2.1 LIFT COEFFICIENT 
4.1.2.2 DRAG COEFFICIENT 

The pitching moment characteristics are identical to those for the body- 
axis system (see Section 4.1.1.3). 

The pertinent equation for obtaining the total coefficient for any given 
flight condition precedes the presentation of data. Each element of the 
equation is defined and referenced to the appropriate figures and/or 
tables for obtaining the corresponding numberlcal values. Where addi- 
tional information is considered beneficial (e.g., aeroelastic deforma- 
tion, hypersonic viscous interaction, and RCS impingement), Appendices 
have been included for reference. 




STABILITY AXIS SYSTEM 



4.1.2- 



SD72-SH-0060-1M 



* 



Rockwell International 

Space Division 



4.1.2.1 LIFT FORCE COEFFICIENT. The Orbiter Vehicle aerodynamic lift force 
coefficient is defined in this section. The basic aerodynamic lift 
force coefficient data are presented 
in three forms: 1 ) as a function of 
angle of attack and Mach number from 
M = 0.25 through M = 20; 2) as a 
function of angle of attack and_the 
viscous interaction parameter (VA) 
from 0.005 (equivalent to M - 13.6) 
through 0.08 (equivalent to 300,000 miaiiv* wind 

feet of altitude; and 3) as a function of angle of attack and 
altitude from 300,000 feet through 600,000 feet. Orbital aerodynamic 
characteristics are included in Appendix C. RCS jet thrust, thrust 
impingement, and flow field changes due to jet plumes are also 
included in this section [4.1.2.1], Uncertainties associated with 
the lift force characteristics are available in Section 6.0. 




The RCS flow field interaction data are presented as a contribution 
to the lift force (L) rather than the coefficient (C|_) since the 
terms due to jet thrust and impingement are independent of dynamic 
pressure and cannot, therefore, be normalized in the conventional 
manner. CAUTION should be observed when applying these terms fn the 
flight regime where the RCS : s used in conjunction with the aerodynamic 
force (cf. Section 3.6); i.e., the aerodynamic coefficient must be 
converted to a dimensional force before adding the RCS flow field 
interaction effect (see also Appendix B) . 

The total lift force is: 

L ■ q" S C. + L„ r , 

TOTAL M L TOTAL *CS 

AERO 



* The total aerodynamic lift force coefficient Is obtained by the 
fol lowing equation: 



C. - C, + [AC. + AC. 1+ AC. + AC. + AC. 

L TOTAL L »ASIC L El£VATOR U All.ERON J El£VCN >- BODY >- RUDDER L 



FLAP 



■SPEED 
BRAKE 



+ C L, W + C U I? + * C L flE ; AC L 
a q nEX 



+ AC. + AC. 

LANDING "-GROUND l-SILTS 



GEAR 



EFFECT 



POO 



where, 

L BASIC 



■ Basic, full-scale, f reestream, rigid (Figures 4.1.2.1-1 
body lift force coefficient. through -6) 

NOTE: 1 . Al 1 control surfaces neutral 
except & st - 25°. 



Refer to Appendix D when using digitized data. 



4.1.2.1-1 



£L 



-L-K-C 



C. 1 m 



'1* 



Rockwell International 

Space Division 



^C ■ Change in lift coefficient due to (Figures 4.1.2.1-7 

Leievator elevon (elevator) deflection, 6 e , through -35) 

when inboard and outboard angles 
are equal . 

NOTE: 1. Partial span factor, K L , to (Figure 4.1.2.1-36) 
be used for elevon-body 
flap interconnect flight 
system where <5 e is 1 i mi ted 
to ±5* and inboard and out- 
board angles are not equal. 

AC L = K L AC L + (1 - K L )AC L 

•l e o 8 

AC m Change in lift coefficient due to 
L ah.eron aileron deflection, 5 a . 



■^f^'-^J^^KJ^ 1 -^.,?^^]-^ 



EVATOR 



AC ■ Change in lift force coefficient due (Figures 4.1.2.1-37 

l «ody to body flap deflection, 5„ . through -66) 

HAP ' r " 

\ 

AC - Change in lift force coefficient due (Assume zero) 

l ruooer to rudder deflection, 5 . 

AC - Change in lift force coefficient due (Figures 4.1.2.1-67 

l speeo to speed brake deflection, 5«._. through -93) 

SRAKE °° 

C ■ Change in lift force coefficient wi th (Assume zero) 

a rate-of-change of angle of attack, a, 

(per radian) . 

C - Change in lift force coefficient with (Assume zero) 

*■ pitch rate, q, (per radian). * 

AC. ■ Change in lift force coefficient due 

FlEX to aeroelastlc deformation. 

- ac[ - (1 - n N )(c* - c* ) BA51C - (l - n Le )(AC« + Ac£ AiLfRON ) 

o ° e 

- (1 - n L ) ac" - (1 - n. ) ac. r 



*For rotary derivative transfer equations see NASA SP-3070, "Summary of .Trans- 
formation Equations and Equations of Motion .Used .in .Free-Flight -and .Wind .Tunnel 
Data Reduction and Analysis," Gainer, T. G. r and S.- Hoffman, Xangley Research 
Center, Hampton, Virginia (1972) . 

4.1 .2.1-2 

^ L; . -::. Li. t C IM 



Space Sy»ttms Group ^J^9 International 



41^ Rockwell 



NOTE: 1. Detailed discussion of aero- 
elasticity may be obtained 
from Appendix A. 

where the flexible (F) to rigid (R) 
ratios are, 

n N - basic lift (^Sure 4.1.2.1-94) 

H t - elevon (Figure 4. 1 .2. 1-95) 

ri t - body flap (Figure 4.1.2.1-96) 

n, - speed brake (Assume 1.0) 

AC' - flexible intercept at a - (Figure A. 1.2. 1-97) 



AC - Change in lift force coefficient due (Figure A. 1.2.1-98) 

Landing t0 extension of landing gear. 

GEAR 

AC. ■ Change in lift force coeffl dent due (Figures A. 1.2. 1-99 

'-ground to proximity of ground. f(h/b). through -108) 

iMtcT r , 

NOTE: 1. See Section l.k for ground 

clearance and scrape attitude. 

AC - Change In lift force coefficient due 

l silts t0 addition of SILTS pod. 

POO 

- 0.0018229 - 0.O019876M + 0.000*01 427M 2 

for M <. 6.0 

- zero for M > 6.0 

*To obtain the RCS flow field Interaction effect on the. lift force 
use; 

l kcs- ( N «c 5 cos a ' A RCS s,n a) * P° unds 

where, N. and A are obtained .from Sections 4.1.1.1 and 4.1.1.2, 
resDectlvely. 



* Refer to Appendix when using digitized data, 



4.1.2.1-3 

£ L '.I-Gh-OCtO 1M 



* 



Rockwell International 

Space ttvMon 



-20 



ALPHA CDEGD 

20 

T — • — i — r 



i — i — r 



-0.5 



CONFIGURATION 



BASELINI CR8ITCR VEHICLE 

CENTER OP GRAVITY XO • rs 1076.7 IN. 

OR YO • BL 0.0 IN. 

rO-EWT REFERENCE ZO • W. 375.0 IN. 



RCFEFCNCE DIMENSIONS 

WING AREA SU - 2690.00 SQ.FT. 

WING SPAN BU ■ 78.056 FT. 

M.A.C. Cw - 39.560 FT. 

BOOY LENGTH LB » 1290.3' IN. 



ALPHA,, (DEO? 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

1*0.000 

N5.000 

50000 



0.250 
A 



0.H0O 

_s 



0.600 



0.800 



MACH Njr-e^R 



0.650 
E 



0.900 

F 



-0.50280 

-0.25906 

-0.15202 

-0 . 05000 

0.0621* 

0.17*53 

0.29705 

0.hO**6 

0.51599 

0.53581 

0.77676 

0.91657 

1 . 0063* 

1.0896* 

< ♦ •♦«• 



-C.5I0S7 

-0.27397 

-0.16199 

-0 • 05000 

0.06212 

0.17HH8 

0.29691 

0.*0S2* 

0.52757 

0.65002 

0.78385 

0-92529 

1.01512 

1.088*6 



-0.52957 

-0.28S70 

-0.17186 

-0.05500 

0.07201 

0.17928 

0.30657 

0.*167* 

0.5*905 

0.67*26 

0.79709 

0.92851 

1.01007 

1.0**89 



-0.58*5* 

-0.32751 

-0.19155 

-0.06500 

0.06176 

0.18859 

"0.31963 

0.**3S* 

0.56*80 

0.68162 

0.79087 

0.89578 

0.9318* 

0.92299 



LIFT COtrriC'gNT 



0.920 
_S 



0.950 

H 



*0 




i.* 



0.930 
_J 






-0.59772 

-0.33790 

-0.19632 

-0 . 06200 

0.06652 

0.19295 

0.31838 

.*H172 

.56566 

.67309 

.77995 

.87690 

.91266 



0.90795 



• • • 

• » 

• • ♦ 
» • • 



-0.61005 

-0.3*601 

-0.20588 

-0.06000 

0.07101 

0.20355 

0.32*13 

0.**572 

0.55794 

0.68323 

0.79*01 

0.89*85 

0.9207* 

0.93837 



• * * ♦• 
t • * • • 



-C62831 

-0.35039 

-0.21553 

-0.06000 

0.07563 

0.21579 

0.3*997 

0.H7690 

0.5e585 

0. 70567 

0.81577 

0.91619 

0.9599* 

0.96751 






0.6551* 
-0. 35697 
0. 21*85 
•0.06000 
0.06*98 
0.239*7 
0.387S3 
0.51887 
. 6*660 
0.7S535- 
0.8650! 
0.96*29 
1 . 00227 
02232 



-0.65616 
-0.36172 

-o. lenss 

-0.05500 
0.09*1* 
0.2*762 
0.38955 
0.52899 
0.66026 
0.777S3 
0.89069 
0.99605 
1.0*837 
1.07573 



• P # # 

• • • « 

• • • • 



ENGINEER 
OATE I 



FIGURE 4.1.2.1 - 1 

BASIC LIFT COEFFICIENT 



4.1.2.1-4 



£ L 



u 



M 



'1* 



Rockwell International 

SpacmC**mon 



'• 5 | I I I I I I I I 



ALPHA (DEG) 
10 10 20 30 

| I I I I | i I I I | i I I I I N I I | 

r i i 'i i i i i i m i i i i i 



a 




-0.5 



-i.o 



0.8 



J. I 1 I I I ' I ' I I I I I I I I I I I I I I I I 1 I 

1.1 1.2 1.3 1.4 1.5 

MACH NUMBER 



COFIGURAT10N 



BASELIhC 0R8ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOttNT REFERENCE ZO - U. 375.0 IN. 



REFERENCE DlftNSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 
BOQY LENGTH IR ■ 1PQ0.3 IN. 



ALPHA (PEG) 



-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

40.000 

45.000 

go ooo 



0.900 

F 



0.920 
G 



0.950 
_fci 



0.980 
I 



MACH NU-9ER 



1.050 
J 



-0.61005 

-0.34601 

-0.20588 

-0.06000 

0.07101 

0.20356 

0.32413 

0.44572 

0.56794 

0.68323 

0.79401 

0.89485 

0.92074 

0.93837 

***** 

***** 

i »•#• 

***** 

*•*» * 



-0.62831 

-0.35039 

-0.21553 

-0.06000 

0.07563 

0.21579 

0.34997 

0.47690 

0.585B5 

0.70567 

0.81577 

0.91619 

0.95994 

0.96751 






-0.65514 

-0.35897 

-0.21485 

-0.06000 

0.08498 

0.23947 

0.38783 

0.51887 

0.64660 

0.76535 

0.86501 

0.96429 

1 . 00227 

1.02232 






-0.65616 

-0.36172 

-0.19888 

-0.05500 

0.09414 

0.24762 

0.38955 

0.52999 

0.66026 

0.77783 

0.89069 

0.99805 

1 .04837 

1.07579 



1. 1 FT COEFFICIENT 



1.100 
_K 



1.200 
.J. 



1.300 
M 



1.500 
N 



-0.64808 

-0.35027 

-0.20310 

-0.04700 

0.10315 

0.25552 

0.39173 

0.53602 

0.66393 

0.78377 

0.89596 

1.00286 

1.06699 

1.10328 



-0.54225 

-0.35695 

-0.19292 

-0.03600 

0.10796 

0.25513 

0.39121 

0.53054 

0.65357 

0.77863 

0.89086 

1.00255 

1.06560 

1.11188 



••»»•»»••»•♦*•••»»•»>*•»•»•••• 



••••••••••••ft********* 

•»•*****•*••••**••» *»• 

*»•••*»•••**•»**••• *U* 

*»»*•••* *j» ****♦•****{»* 



••**•»*•» 
•*»•***•* 
********* 
****** 



-0.61158 

-0.33449 

-0.18275 

-0 . 02500 

0.10460 

0.25014 

0.38627 

0.51767 

0.63927 

0.75952 

0.85608 

0.95636 

1.03541 

1.09985 






-0 

-0 

-0 

-0 

















1 
1 

t ft* 
>*«• 
> » *• 
> »»» 

*♦• 



57681 
30454 
16775 
02300 
,10295 
,24043 
.37178 
,49146 
,61835 
.72667 
.83073 
.92538 
.00114 
.07176 
»****• 
»•»*** 
»*•**• 
»•• »•• 
►*•»•• 



-0 . 48844 

-0.25188 
-0.12989 
-0.01500 
0.09317 
0.21606 
0.32805 
0.42874 
0.54671 
0.64381 
0.74311 
0.83834 
0.91858 
0.99205 



ENGINEER 
DATE I 



FIGURE 4.1.2.1 - 2 

BASIC LIFT COEFFICIENT 



4.1.2.1-5 



£E72-s;-i-ccec im 



Rockwell International 

Spac* Division 




-10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

MO. 000 

45.000 

so ooo 



-0.64225 

-0.35585 

-0.19292 

-0 . 03500 

0.10796 

0.25513 

0.39121 

0.53054 

0.6S357 

0.77863 

0.89086 

1.00255 

1.06660 

1.11188 






-0.61158 

-0.33449 

-0.18275 

-0 . 02500 

0.10460 

0.25014 

0.38627 

0.51767 

0.63927 

0.75952 

0.85608 

0.95636 

1.03541 

1.09985 



-0.57681 

-0.30454 

-0.16776 

-0.02300 

0.10295 

0.24043 

0.37178 

0.49146 

0.61835 

0.72667 

0.83073 

0.92538 

1.00114 

1.07176 



-0.48844 

-0.25188 

-0.12989 

-0.01500 

0.09317 

0.21506 

0.32805 

0.42874 

0.54671 

0.64381 

0.74311 

0.83834 

0.91858 

0.99205 






-0.36885 

-0.19695 

-0.09888 

-0.01700 

0.08419 

0.16125 

0.24173 

0.33103 

0.41958 

0.50777 

0.50244 

0.68871 

. 76904 

0.84561 

0.99835 



-0.31514 

-0.16705 

-0. 10455 

-0 . 04290 

0.02995 

0.10458 

0.I8S06 

0.27135 

0.35229 

0.43483 

0.52033 

0.50168 

0.57886 

0.76551 

0.91B67 



-0.29383 
-0.16822 
-0.10504 
-0.03700 
0.02043 
0.08600 
0.15609 
0.22523 
0.29513 
0.36604 
0.4H227 
0.52215 
0.60751 
0.68386 
0.84307 
0.97219 
1.07919 
1 . 15675 

I * • » t * t • ••» 



22874 
-0.13893 
-0.10050 
-0.04430 
0.011)1 
0.06174 
0. 11881 
0.18185 
0.24730 
0.31897 
0.39229 
0.46559 
0.53159 
0.61884 
0.76946 
0.89530 
1 .00341 
1.07904 



ENGINEER 

DATE. 



FIGURE 4.1.2.1 - 3 

BASIC LIFT COEFFICIENT. 



U. 1.2. 1-6 



f ; 



C i IV] 



#1% 



Rockwell International 

Space OivMon 



ALPHA CDEGD 

SO 20 40 60 

I I I I I I I 



o 




-0.2 



-0.4 



10 12 IH 16 

MACH NUMBER 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO » FS 1075.7 IN. 
OR YO - BL 0.0 IN. 

MOENT REFERENCE 20 - M. 375.0 IN. 



REFERENCE DII-ENSIONS 

WING AREA SW - 2630.00 SQ.FT. 

WING SPAN BW - 78.056 FT. 

M.A.C. CU - 39.560 FT. 

BUOY LENGTH I, R - 1390.3 IN. 



*LP"A <PE9> 



■10.000 

-5.000 

-2.500 

0.0 

2.500 

5.000 

7.500 

10.000 

12.500 

15.000 

17.500 

20.000 

22.500 

25.000 

30.000 

35.000 

HO. 000 

45.000 

50-000 



2.000 




2.500 

P 



3.000 
_Q 



4.000 
R 



MACH NUMBER 



5.000 

_s_ 



-0.36885 

-0.19695 

-0.09888 

-0.01700 

0.08419 

0.16125 

0.24173 

0.33103 

0.41958 

0.50777 

0.50244 

0.6S871 

0.76904 

0.84551 

0.99835 



-0.31514 
-0.16705 
-0.10456 
.04290 
.02995 
.10468 
.18906 
.27135 
.35229 
0.43483 
0.52033 
0.60168 
0.67886 
0.76551 
0.91867 



-0. 

0. 
0. 
0. 
0. 
0. 



-0.29383 
-0.16922 
-0.10504 
-0.03700 
0.02048 
0.08600 
0.15609 
0.22528 
0.29513 
0.36604 
0.44227 
0.52215 
0.60751 
0.68386 
0.84307 
0.97219 
1.07919 
1.15675 



-0.22874 
-0.13893 
-0.10050 
-0.04430 
0.01111 
0.06174 
0.11881 
0.18185 
0.24730 
0.31897 
0.39229 
0.46559 
0.53159 
0.61884 
0.76946 
0.89630 
1.00341 
1.07904 



LIFT CCCFFIC1ENT 



-0.19854 
-0.12424 
-0.09081 
-0.04724 
0.00642 
0.04301 
0.09656 
0.15220 
0.21351 
0.27892 
0.35079 
0.42351 
0.49654 
0.57019 
0.72044 
0.84607 
0.96129 
1.03683 
1-08629 



8.000 

T 



10.000 

_JJ 



15.000 



20.000 
w 



-0.18641 

-0.12402 

-0.08913 

-0.05540 

-0.02023 

0.01774 

0.05965 

0.10604 

0.16115 

0.22632 

0.29998 

0.36492 

0.44356 

0.51805 

0.66845 

0.79881 

0.91017 

0.98747 



-0.18641 

-0.12402 

-0.08913 

-0 . 05540 

-0.02023 

0.01754 

0.05558 

0.10002 

0.15328 

0.21732 

0.29043 

0.35587 

0.43474 

0.50936 

0.64465 

0.78362 

0.88400 

0.96803 

1-02007 



-0.18641 

-0.12402 

-0.08913 

-0.05540 

-0.02023 

0.01754 

0.05558 

0.10002 

0.15328 

0.21732 

0.29043 

0.35587 

0.43474 

0.50936 

0.64465 

0.78382 

0.88400 

0.96803 

1.02007 



-0.18541 

-0.12402 

-0.08913 

-0.05540 

-0.02023 

0.01754 

0.05558 

0.10002 

0.15328 

0.21732 

0.29043 

0.35587 

0.43474 

0.50936 

0.644S5 

0.78382 

0.88400 

0.96903 

1 .02007 , 



ENGINEER 
..BKJZ 



FIGURE 4.1.2.1 - 4 

■ BASIC LIFT COEFFICIENT 



4.1.2.1-7 



£E72-SH-CC60 1M 



*x 



t^ HocKweii international 

Space Division 



I -2ri ; | i I I I I 1 



1.0 



o.e 



CJ 



0.6 



0.4 



i-'in 



0.2 



I M i I I I I i I I I II I i 1 > 




ALPHA CDEG3 

£0 30 40 50 

f I I I I | I I ! I | I I II | 

! I I I I I i II 



.02 



iillillliiiilll lll llliliiiillll'lllllllllll ll llll 
.04 .05 .OS .07 .08 .09 .10 .11 .12 

VBAR 



i i i 



.03 



.13 



CONFIGURATION 



BASELINE ORSITER VEHICLE 



CENTER Of GRAVITY 

OR 
K>-ENT REFERENCE 



XO = FS 1075. 7 IN. 
YO - En. 0.0 IN. 

20 = UL 375.0 IN. 



IN 

REFERENCE DIMENSIONS 






wise 


AREA 


SW «■ 


2690.00 


SO. 


FT. 


wing 


SPAN 


BW " 


78.056 


FT. 




M.A.C. 


CW = 


3S.56C 


FT. 




BODY 


LENGTH LB ' 


1290.3 


IN. 







VBAR 




0.005 


0.010 


. 020 


0.040 


0.060 


0.080 


ALPHA (DtGI 


A 


B 


C 


D 


E 


F 




VI 


SCOUS LIFT 


CCCFFIC1ENT 






20 . 000 


. 35587 


. 35365 


. 34920 


0.34031 


0.33141 


0.32252 


25.000 


.0.5097-6 


0.50645 


0.50057 


0.48837 


0.47712 


0.4654 1 


30.000 


0.6t465 


0.64085 


0.6333C 


0.5ie20 


0.6C31C 


0.58=0 C 


35.000 


0.7E3S; 


0."779sC 


0.7707- 


0.75342 


0.73c!C 


0.7!87S 


40.000 


0.88400 


0.87912 


0.85935 


0.84974 


. 63020 


0.6)000 


45.000 


0.96303 


0.96322 


0.95357 


0.9345! 


0.91542 


0.89625 


50.000 


\ . UC. \J'J I 


1 .0157F 


1 . 007oe 


0.98965 


. 9723-t 


G.S-.-^:-': 



F'GJ"-F 4.1.2. I- 1 



f r 7 2-sh-cccc im 



#Jt 



Rockwell International 

SpacaDtaaion 



ALPHA CDEG) 
20 40 60 

I I I I I I I I I 




350000 



400000 



450000 



500000 550000 600000 650000 700000 750000 

ALTITUDE CFT.D 



CCNFIGURA1 
BASELINE CRBITER VEHICLE 


'ICN 




RLj-LKENCE UIMiNSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


HING AREA SW - 2590.00 


SO. FT. 


OR YO - BU 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MCtCNT REFERENCE 20 - U. 375.0 IN. 


M.A.C. CM - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 





ALTITUDE (FT.) 




300000.0 


350000.0 


400000.0 


H50000.0 


500000.0 


550000.0 


600000.0 


ALPHA (0EG1 


A 


B 


C 





E 


F 


G 






HIGH ALTIT 


UCE LIFT CO 


EFFICIENT 






20.000 


0.32252 


0.23081 


0.13520 


0.08407 


0.06477 


0.05860 


0.05764 


25.000 


0.46541 


0.327H2 


0.18349 


0.10660 


0.0774H 


0.05827 


0.06582 


30.000 


0.5SS00 


0.41010 


0.22452 


0.12553 


0.08800 


0.07605 


0.07427 


35.000 


0.71878 


0.49737 


0.26641 


0.14300 


0.09631 


0.08150 


0.07921 


40.000 


0.81060 


0.55805 


0.29484 


0.15402 


0.10082 


0.08392 


0.08133 


45.000 


0.89626 


0.6138H 


0.319H7 


0.16193 


0.10239 


0.08351 


0.08061 


50.000 


0.954H2 


0.55121 


0.33515 


0.16608 


0.10218 


0.08186 


0.07873 



ENGINEER JHASA_ 
DATE 



FIGURE 4.1.2. 1 - 6 

BASIC LIFT COEFFICIENT 



4.1.2.1-9 



it 



5 H - C C C 



1M 



'1* 



Rockwell International 

Sp*c* Divwton 



MACH NUMBER 



0.250 



DELE CDEGD 

-50 -25 25 

| I I I I | I I I i | i I I I t 
MM 



UJ 
_! 
(_> 
Q 




| ||MllllllMI 

-5 5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELINE ORBITER >£HICLE 

CENTER OF GRAVITY XO - F5 1076.7 IN. 

OR YD - BL 0.0 IN. 

rCtCM REFERENCE ZO - H. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2690.00 SQ.FT. 
WINS SPAN BW » 78.056 FT. 
M.A.C. CW - 39.560 FT. 

BODY LENOTH L3 - 1290.3 IN. 



DELE (OEG) 



-**0.000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA tCEGl 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 




10.000 

E 



15.000 

F 



20.000 
G 



25.000 
H 



ELEVCN LIFT INCREMENT 



-0.41900 

-0.39700 
-0.37800 
-0.36300 
-0.34900 
-0.29500 
-0.20700 
-0.10000 
0.0 

0.09600 
0.19400 
0.29400 
0.38700 



-0.41300 
-0.39500 
-0.37400 
-0.35400 
-0.33100 
-0.29500 
-0.20800 
-0.09800 
0.0 

0.09300 
0.18900 
0.28000 
0.38200 



-0.39900 
-0.39100 
-0.37800 
-0.36300 
-0.34100 
-0.28800 
-0.19000 
-0.10000 
0.0 

0.09500 
0.18800 
0.28800 
0.38200 



-0.38900 
-0.38700 
-0.38300 
-0.37200 
-0.35300 
-0.29400 
.19800 
.09800 
.0 

.08800 
.18400 
0.27500 
0.36900 



-0. 
-0. 

0. 

0. 

0. 



-0.40900 
-0.40100 
-0.39200 
-0.38300 
-0.36900 
-0.29300 
-0.19700 
-0.09800 
0.0 

0.08800 
0.18400 
0.27500 
0.36900 



-0.43000 
-0.42800 
-0.42200 
-0.40900 
-0.38400 
-0.28600 
-0.19200 
-0.09800 
0.0 

0.0680C 
0.18400 
0.27500 
0.36900 



-0.47500 
-0.49000 
-0.48800 
-0.49000 
-0.40000 
-0.29700 
-0.19700 
-0.10000 
0.0 

0.08500 
0.17400 
0.2S300 
0.35200 



-0.51000 
-0.51500 

-0.50600 
-0.43500 
-0.36300 
-0.28700 
-0.19000 
-0.10000 
0.0 

0.07200 
0.15000 
0.22900 
0.31000 



ENGINEER S^ 
OATE„?/2; 



FIGURE 4.1.2.1-7 „^- v , T 

ELEVGN LIFT COEFFICIENT INCREMENT 



W 



4.112.1-10 



L 



L v. L L 



M 



<1* 



Rockwell International 

SpacaDMaion 



X 



MACH NUMBER 



0.400 



DELE CDEG) 

-50 -25 _0 25 

1 I I i | I I i I | I I i i 
I I I I 



W 

8 




ALPHA CDE6D 



CONFIGURATION 



BASELINE 0R3ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOfCNT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW - 2S90.00 SQ.FT. 
WING SPAN BU ■ 78.055 FT. 
M.A.C. CW • 39.550 FT. 

BODY LENGTH LB - 1290.3 IN, 











ALPHA 


<CEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


na,r <oeg) 


A 


B 


C 


D 


E 


F 


G 


H 








ELEVON LIFT 


INCREMENT 








-40.000 


-0.41900 


-0.41300 


-0.39900 


-0.38900 


-0.40900 


-0. 43000 


-0.47500 


-0.51000 


-35.000 


-0.39700 


-0.39500 


-0.39100 


-0.38700 


-0.40100 


-0.42800 


-0.49000 


-0.51500 


-30.000 


-0.37800 


-0.37400 


-0.37800 


-0.38300 


-0.39200 


-0.42200 


-0.48800 


-0.50600 


-25.000 


-0.36300 


-0.35400 


-0.35300 


-0.37200 


-0.38300 


-0.40900 


-0.49000 


-0.43600 


-20.000 


-0.34900 


-0.33100 


-0.34100 


-0.35300 


-0.36900 


-0.38400 


-0.40000 


-0.36300 


-15.000 


-0.29500 


-0.29500 


-0.28800 


-0.29400 


-0.29300 


-0.28600 


-0.29700 


-0.28700 


-10.000 


-0.20700 


-0.20800 


-0.19000 


-0.19800 


-0.19700 


-0.19200 


-0.19700 


-0.19000 


-5.000 


-0.10000 


-0.09800 


-0.10000 


-0.09800 


-0.09300 


-0.09800 


-0.10000 


-0.10000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.09600 


0.09300 


0.09500 


0.08800 


0.08800 


0.08800 


0.08500 


0.07200 


10.000 


0.19400 


0.18900 


0.18800 


0.18400 


0.18400 


0.18400 


0. 17400 


0.15000 


15.000 


0.28400 


0.28000 


0.28800 


0.27500 


0.27500 


0.27500 


0.26300 


0.22900 


20.000 


0.38700 


0.38200 


0.38200 


0.36900 


0.36900 


0.36900 


0.35200 


0.31000 



ENGINEER 
OATE 



™d£& 



?r 



FIGURE 4. 
£LEV3N LIFT 



1.2.1-8 

COEFFICIENT INCREMENT 



ii.1.2.1-11 



SE'2-SK-GCeC IM 



'1* 



Rockwell International 

Spaca Division 



MACH NUMBER 



0.600 



CDEGD 

25 



Ll) 

u 

a 




-.4 



-.6 



5 
ALPHA CDEGD 



CONFIGURATION 



BASELINE 0R81TER VEHICLE 

CENTER CT GRAVITY XO • FS 1076.7 IN. 

OR YO - SL 0.0 IN. 

MOtCNT REFERENCE 20 • WL 375.0 IN. 



REFERENCE OIh€N5ICNS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW ■ 78.056 FT. 
M.A.C. CW - 39.560 FT. 

eCOY LENGTH LB " 1290.3 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


pn f tnrr,) 


A 


B 


C 


D 


E 


F 


G 


H 








ELEVCN LIFT 


INCREMENT 








-40.000 


-0.43500 


-0.37200 


-0.34200 


-0.35000 


-0.37200 


-0.34500 


-0.37300 


-0.27100 


-35.000 


-0.42200 


-0.36700 


-0.34000 


-0.35200 


-0.37400 


-0.35400 


-0.37800 


-0.27900 


-30.000 


-0.40300 


-0.35600 


-0.33600 


-0.34500 


-0.36700 


-0.35700 


-0.37SOO 


-0.28200 


-25.000 


-0.37500 


-0 . 3H200 


-0.33000 


-0.33300 


-0.35400 


xO. 36000 


-0.36600 


-0.27500 


-20.000 


-0.33100 


-0.31000 


-0.30600 


-0.31500 


-0.33500 


-0.34400 


-0.33300 


-0.25500 


-15.000 


-0.27700 


-0.26300 


-0.25100 


-0.27000 


-0.2B600 


-0.27200 


-0.25500 


-0.22000 


-to. 000 


-0.19500 


-0.19000 


-0.18600 


-0.19100 


-0.19500 


-0.19000 


-0. 16800 


-0.15600 


-5.000 


-0.09600 


-0 . 09600 


-0.09500 


-0.09400 


-0.09800 


-0.09000 


-0.08600 


-0.07900 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 ■ 


0.0 


5.000 


0.08300 


0.09500 


0.09000 


0.09300 


0.09500 


0.09400 


0.08000 


0.06400 


10.000 


0.17500 


0.1S200 


0.18300 


0.18700 


0.20000 


0.18000 


0.15700 


0.11700 


15.000 


0.26000 


0.26700 


0.26500 


0.27500 


0.29600 


0.26400 


0.24400 


0.15100 


20.000 


0.3^900 


0.34500 


0.34UQ0 


0.35600 


0.38500 


C. 30900 


0.29SG0 


0.19900 



ENGINEER 
0ATE__&ZZy/2g- 



FIGURE 4. 
ELEVONLIfT 



1.2.1-9- 

COEFFICIENT INCREMENT 



\_y 



24.1.2.1-12 



I I 



vX.oC IM 



€> 



Rockwell International 

SpwMOMnon 



JL" 



MACH NUMBER 



0.800 



DELE CDEG) 

-50 -25 25 

I I II i I I i I I M I I I 



UJ 
Q 



-.4 




-eo 



-15 



ALPHA CDEG) 



CO*" I CURAT I ON 



BASELINE OR9ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR YO • EC 0.0 IN. 

I-O-ENT REFERENCE ZO • W_ 375.0 IN. 



REFERENCE OIf€NSICfS 
WING AREA 5W - 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW » 39.560 FT. 

BCOY LENGTH LB ■ 1290.3 IN. 











ALPHA 


<DEG> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


rcu (neo) 


A 


B 


c 





E 


F 


G 


H 








ELEVON LIFT 


!NCR£>€NT 






, , 


-40.000 


-0.42600 


-0.43300 


-0.39300 


-0.38400 


-0.37400 


-0.28700 


-0.19300 


-0.13500 


-35.000 


-0.41700 


-0.40700 


-0.37200 


-0.36300 


-0.34700 


-0.26600 


-0.19000 


-0.14600 


-30.000 


-0.40200 


-0.37000 


-0.34400 


-0.33700 


-0.31500 


-0.24500 


-0.18700 


-0.15500 


-25.000 


-0.37600 


-0.33300 


-0.30700 


-0.30400 


-0.27800 


-0.22500 


-0.13400 


-0.16100 


-20.000 


-0.32900 


-0.29500 


-0.26300 


-0.25700 


-0.23900 


-0.20500 


-0.17900 


-0.16200 


-15.000 


-0.25400 


-0.24000 


-0.21300 


-0.22900 


-0.20300 


-0.18800 


-0.17100 


-0.15600 


-10.000 


-0.16500 


-0.18000 


-0. 16000 


-0.17500 


-0.16500 


-0.16200 


-0.14700 


-0.13400 


-5.000 


-0.08700 


-0.10400 


-0.09500 


-0.10100 


-0.09500 


-0.08500 


-0.07500 


-0 . 07500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.07800 


0.09500 


0.09400 


0.09900 


0.08800 


0.09000 


0.07900 


0.06000 


10.000 


0.15300 


0.18000 


0.18400 


0.20000 


0.18500 


0.17500 


0.15200 


0. 10! 00 


15.000 


0.22300 


0.24800 


0.27400 


0.27900 


0.25800 


0.23300 


0.21100 


0.12900 


20.000 


0.29900 


0.31000 


. 32200 


0.34700 


0. 30500 


0.27000 


0.25200 


C . 14500 



ENGINEER £&> 

IQATE lTikJ31 



FIGURE 4. 

ELEVON LIFT 



1.2.1- 

COEPF 



10 
ICIENT 



INCREMENT 



4.1.2.3-13 



JL72 



ccec im 



'1* 



Rockwell International 

Space Divwon 



MACH NUMBER 

• trrn 



DELE CDE3D 

-50-25 25 

t— r 



UJ 

u 
o 




-.4 



ALPHA CDEGD 



BASELINE 0RS1TER VEHICLE 
CENTER CF GRAVITY XO - FS 1076.7 
OR YO • BL 0.0 

MOENT REFERENCE ZO - WL 375.0 



OJRA 


TION 






RtFErENCE Qir£N5I0N5 




IN. 


UING AREA SW ■ 2690.00 


SQ.FT. 


IN. 


WING SPAN BU • 78.056 


FT. 


IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB • 1290.3 


IN. 











ALPHA 


(DEG! 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 








ELEVCN LIFT 


INCREMENT 








-HO. 000 


-0.41000 


-0.38200 


-0.38200 


-0.40000 


-O.2S0O0 


-0.18800 


-0.13700 


-0. 1140C 


-35.000 


-0.40400 


-0.3TH00 


-0.37300 


-0.37000 


-0.25900 


-0.17700 


-0.15700 


-0. 12900 


-30.000 


-0.39200 


-0.35400 


-0.35300 


-0.33400 


-0. 22500 


-0.16600 


-0.17100 


-0.14000 


-25.000 


-O.3SSO0 


-0.32200 


-0.32000 


-0.29000 


-0.19300 


-0.15600 


-0.13200 


-0. 14800 


-20.000 


-0.32900 


-0.2B000 


-0.27600 


-0.24000 


-0.16000 


-0.14600 


-0.18600 


-0.15000 


-15.000 


-0.25500 


-0.22800 


-0.22800 


-0.1 8600 


-0.12900 


-0.13200 


-0.17900 


-0.14500 


-10.000 


-0.17200 


-0.16500 


-0.16200 


-0.12500 


-0.09500 


-0.1 1100 


-0.14700 


-0.12100 


-5.000 


-0.08100 


-0.09100 


-0.08000 


-0 . 05300 


-0.05700 


-0 . 06600 


-0.07500 


-0.0610C 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.06400 


0.08000 


0.07000 


0.07700 


0.06000 


0.08600 


0.06400 


. 05700 


10.000 


0.13800 


0.14100 


0.14500 


0.18200 


0.18700 


0.17300 


0.14000 


0.09100 


15.000 


0.20100 


0.20100 


0.21700 


0.26300 


0.26300 


0.23300 


0.20203 


. 1 11 00 


20 . 000 


0.24100 


0.25000 


0.28500 


0.33500 


. 32000 


0.26400 


0.24100 


o . : i 7oc 



ENGINEER £f^ __ 
DATE...<22^g?g 



FIGURE 4. 
ELEVON LIFT 



1.2. 1-11 

mFFFTCTENT INCREMENT 



4.1.2. 1-U 



f,',CC iM 



* 



Rockwell international 

SpacaOMsnn 



JT-- 



MACH NUMBER 

• H ' ■ ' ! ' 'I I I I 



0.950 



8 



Mil 



x l i I I I I I I I I 



I (I I 



rrr i 




DELE CDEGD 

-50-25 25 

| I I I , | I I 1 | > I i I t 

TTT 



I i I 



I I. I I I I 1 



L.I I I I 1 1 1 1 



T 



TTT 



I..I I. I ! 1 I 1 



-20 



-15 



•10 



5 10 

ALPHA CDEG) 



15 



20 



CONFIGURATION 


BASELIKE 0RBITER VEHICLE 


REFERENCE DIh€N5I0NS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.055 FT. 


K*ENT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BODY LENGTH LB « 1290.3 IN. 



ENGINEER QCC 
DATE 3JI&.T3. 



FIGURE 4. 
ELEVON LTFT 



1.2.1-12 

COEFFICIENT 



INCREMENT 



30 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25. 000 


OELE (DEG) 


A 


B 


C 





E 


F 


G 


H 








ELEVON LTFT 


INCFEreNT 








-HO. 000 


-0.41100 


-0.37700 


-0.37300 


-0.41200 


-0.29100 


-0.20000 


-0.14000 


-0.11500 


-35.000 


-0.39700 


-0.37100 


-0.37500 


-0.3S200 


-0.2B000 


-0.19000 


-0. 15BO0 


-0.13000 


-30.000 


-0.38000 


-0.35500 


-0.36700 


-0.35100 


-0.25S00 


-0.17900 


-0.17400 


-0.14200 


-25.000 


-0.35400 


-0.32600 


-0.34500 


-0.32100 


-0.23100 


-0.16500 


-0.18500 


-0.15200 


-20.000 


-0.31300 


-0.28800 


-0 . 30900 


-0.27000 


-0.19500 


-0.14700 


-0. 19000 


-0.15600 


-15.000 


-0.24200 


-0.24200 


-0.26000 


-0.20700 


-0.15500 


-0.12900 


-0.17700 


-0. 14900 


-10.000 


-0.1S500 


-0.18200 


-0.19300 


-0.13900 


-0.10900 


-0.10200 


-0.13100 


-0.1 1600 


-5.000 


-0.08500 


-0.09100 


-0 . 09500 


-0.06500 


-0.05700 


-0.05700 


-0.06700 


-0.05900 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.07000 


0.05200 


0.05000 


0.06400 


0.07300 


0.07300 


0.07100 


0.05700 


10.000 


0.14300 


0.09800 


0.11300 


0.14700 


0.16900 


0.14500 


0.13100 


0.08800 


15.000 


0.19200 


0.15900 


0.18400 


0.22500 


0.24800 


0.20000 


0. 17100 


0.I04C0 


20.000 


0.23100 


0.23000 


0.26500 


0.30500 


0.30900 


0.24300 


0.19900 


0.11200 



k. 1.2. 1-15 



S D 7 2 - S I-. - C L O 



'i* 



Rockwell International 

Space Division 



MACH NUMBER 



_j 
u 
a 




-.4 



-.6 



-20 



-15 



-10 



5 10 

ALPHA CDEG) 



15 



20 



COTf 1GURATI0N 



BASELINE OR81TER VEHICLE 
CENTER OF GRAVITY XO » FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

M»€NT REFERENCE ZO • W- 375.0 IN. 



REFERENCE DIMENSIONS 
WING AREA SW • 3690.00 SQ.FT. 
WING SPAN BU • 78.056 FT. 
M.A.C. CW « 33.560 FT. 

9QOY LENGTH LE - 1290.3 IN. 



DELE (DEG) 



-40.000 

-35.000 

-30.000 

-25-000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA CCEG) 



-10.000 
A 



-5.000 

3 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



ELEVON LIFT INCREMENT 



-0.40823 
-0.39188 
-C. 37280 
-0 34511 
-0.30422 
-0.23728 
-0.16315 
-0.08557 
0.0 

0.07360 
0.14548 
0. 18794 
0.2178C 



-0.36815 
-0.36309 
-0.34889 
-0.32512 
-0.28937 
-0.24452 
-0.17531 

.08242 

.0 

.05224 

.10082 
0. 15772 
0.21252 



-0 

-0 

-0 

-0 

-0 

-0 

-0 

-0 













36669 
35699 
3537- 
3462b 
30991 
24602 
,17902 
.08718 
.0 

.05050 
.11294 
.18128 
.25048 



-0.39736 
-0.38608 
-0.36495 
-0.32948 
-0.27541 
-0.20816 
-0.13601 
-0.067S2 
0.0 

0.06249 
0.14282 
0.21910 
0.30407 



-0.30243 
-0.29282 
-0.27472 
-0.24817 
-0.21000 
-0.16577 
-0.11471 
-0.05689 
0.0 

0.07152 
0.16087 
0.23961 
0. 30730 



-0.21322 
-0.20250 



.18996 

.17379 
.15336 
.13068 
.10016 
-0.05404 
0.0 

0.06955 
0.13990 
0.19653 
0.24617 



-0.15719 
-0.15809 
-0.17692 
-0.18325 
-0.17905 
-0.16337 
-0.12140 
-0.06364 
0.0 

0.07)06 
0.;2538 
0.1532" 
0. 186M 



.13353 

14263 

14880 

154C3 

.15485 

,14208 

.1111" 

-0.0582? 

0.0 

. 0570C 
0.08739 
0.1017! 
. 1 1 022 



r 



ENGINEER &&> 

date aJHTJl 



FIGURE 4. 
ELEVON LIFT 



1.2.1- 

COEFF 



13 

ICIENT 



INCREMENT 



U. 1.2. 1-16 



i i 



* 



Rockwell International 

Space Ot«ion 



JS 



MACH NUMBER 



1.050 



DELE CDEG) 

-50-25 25 

I i i i i I i i i i I i i i ; I 



_l 
8 



-.4 



I I I I I I I 



...t 



_ 6 LL_L_L_l_L_L_L_i 

'-eo -is 



111! 



I i I 



I I I I I 1 ! I I I I I I 




I I I I I I I II ! I I I I I I l 



_L_L 



J_J_ 



II I I . I I I 



^: 



J_L_L 



■10 



5 10 

ALPHA CDEG) 



15 

> 



20 



30 



COFIOJRA1 
BASELINE ORBITER VEHICLE 


rioN 




F&FEJOCL 01fEN5I0N5 


CENTER OF GRAVITY XO • FS 1076.7 IN. 


WING AREA SW • 2590.00 


SO. FT. 


OR YO - a. 0.0 IN. 


WING SPAN BU « 78.055 


FT. 


MOMENT REFERENCE 20 - U_ 375.0 IN. 


M.A.C. CH • 39.560 


FT. 




BODY LENGTV LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


K.000 


DELE (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






ELEVCN LIFT 


INCRETENT 


-HO. 000 


-0.40000 


-0.34200 


-0.35100 


-0.35200 


-0.34000 


-0.25000 


-0.21000 


-0.19100 


-35.000 


-0.37900 


-0.33900 


-0.34600 


-0.34900 


-0.32300 


-0.23700 


-0.20000 


-0.18200 


-30.000 


-0.35600 


-0.33000 


-0.33700 


-0.33900 


-0.29800 


-0.21900 


-0.18500 


-0.17000 


-25.000 


-0.32400 


-0.31300 


-0.31800 


-0.31400 


-0.26500 


-0.19800 


-0.17000 


-0.15700 


-20.000 


-0.28400 


-0.27900 


-0.27600 


-0.25700 


-0.22300 


-0.17400 


-0.15100 


-0.14100 


-15.000 


-0.22900 


-0.23000 


-0.20900 


-0.19300 


-0.17400 


-0.13800 


-C. 12800 


-0.12100 


-10.000 


-0.15100 


-0.15000 


-0.14000 


-0.12700 


-0.11800 


-O.09B00 


-0.09900 


-0.09500 


-5.000 


-0.08300 


-0.05600 


-0.06200 


-0.06500 


-0.05600 


-0.05000 


-0.05700 


-0 . 05700 


0.0 


0.0 


0-0 


0.0 


0.0 


0.0 


0.0 


0.0 


O.C 


5.000 


0.0B200 


. 06000 


C. 05700 


0.06000 


0.07000 


0.06400 


0.06300 


0.05700 


10.000 


0. 14800 


0.12100 


0.12300 


0.14000 


0.14600 


0.13300 


0.11200 


, C3700 


15.000 


0. 18000 


0.16000 


0. 18500 


0.21800 


0.22300 


0.20000 


0. 14300 


. C9900 


20.000 


0.18700 


0.17500 


0.24800 


0.31800 


0.30600 


0.26800 


0.16600 


0. 13700 



ENGINEER JS«?_ 
DATE £JJ3Ll$- 



FIGURE 
ELEVON L 



4.1.2.1- 

IFTCQEFF 



ICIENT 



INCREMENT 



4.1.2.3-17 



SE72-SH-CCCC 1M 



* 



Rockwell International 

Space Division 



MACH NUMBER 



1.100 



DELE CC : :G3 

-50 -25 25 

i I I I | I I i ■ ! i < ■■ ': I 
TTT 



uj 



u 

Q 




-.H 



-.6 



-50 



5 10 

ALPHA CDEG3 



CONFIGURATION 



BASELlbE 0R8ITER VEHICLE 

CENTER Of GRAVITY XD • F5 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOMENT REFERENCE ZO - U- 375.0 IN. 



REFERENCE D!^E^EIONS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW » 79.055 FT. 
M.A.C. CU • 33.560 FT. 

BCOY lENGTH LB - 1290.3 IN. 



ALPHA (PEG) 



DELE (PEG) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-50.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



■10.000 
A 



-5.000 
S 



0.0 
C 



5.000 
D 



10.000 
E 



15.000 

F 



20.000 
G 



25.00C 
H 



ELEVON LIFT INCREhENT 



-0.39800 
-0.37700 
-0.34800 
-0.31000 
-0.26H00 
-0.21200 
-0.15000 
-0 . 07900 
0.0 

0.05300 
0.10H00 
0.14100 
0.16500 



-0.35000 
-0.34700 
-0.32800 
-0.29500 
-0.25100 
-0.19600 
-0.13000 
-0.05500 
0.0 

0.05400 
0.11200 
0.15500 
0.20000 



-0. 

-0. 

-0. 

-0 

-0 

-0 

-0 

-0 













.35000 

.33H00 

.31000 

.27900 

.23400 

.18200 

. 12000 

.05500 

.0 

.05300 

. 1 1 1 00 

. 1S700 

.22300 



-0.34000 
-0.31500 
-0.29100 
-0.25200 
-0.22300 
-0.17500 
-0.12300 
-0.CS700 
0.0 

0.05700 
0.12700 
0.18900 
0.25000 



-0.29800 
-0.28100 
-0.2S300 
-0.23800 
-0.20400 
-0.16000 
-0.10700 
-0.05000 
0.0 

0.06400 
0.13700 
0.21900 
0.30000 



-0.24200 
-0.22300 
-0.20COO 
-0.17700 
-0.15100 
-0.12400 
-0.09200 
-0.04800 
0.0 

0.05500 
0.12000 
0.17300 
0. 22000 



-0.20500 
-0.19000 
-0.17200 
-0.15400 
-0.13400 
-0.11100 
-0 . 08300 
-0.04600 
0.0 

0.05300 
. 1 0900 
0.136CO 
0. 15->C0 



-0.1880C 
-0.17300 
-0.15B00 
-0.14200 
-0.12400 
-0.10400 
-0.08000 
-0 . 0480C 
0.0 

. 0520C 
. 0830C 
0.0980C 
0.10200 



ENGINEER &£0_ 



FIGURE 4, 
ELEVEN LIF' 



1.2.1-15 

pflpr—TfTFNT INCREMENi 



4.1.2.1-18 



C ! 



'1* 



Rockwell International 

Spac*D)viMon 



_L 



MACH NUMBER 
■ v * 1 l l i I I I I I I I I I 



1.200 



DELE CDEG) 

-50-25 

I I I I | I I 



as 



UJ 

_J 




5 10 

ALPHA CDEG3 



CONF IGLRAT1CN 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR YO.« BL 0.0 IN. 

MOTENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE 0I^EN5IC^S 
WING AREA 34 - 5690.00 SQ.FT. 
WING SPAN BW • 78.056 FT. 
M.A.O CW - 39.550 FT. 

BCOY LENGTH LB - 1590.3 IN. 





— 






ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELE (CEG) 


A 


B 


C 


D 


E 


F 


G 


H 








ELEVEN LIFT 


INCREI^NT 








-40.000 


-0.39100 


-0.36200 


-0.33800 


-0.30400 


-0.26300 


-0.23200 


-0.19400 


-0.17200 


-35.000 


-0.35900 


-0.33000 


-0.30700 


-0.27600 


-0.24300 


-0.20900 


-0 . 1 7700 


-0.1S200 


-30.000 


-0.31900 


-0.29600 


-0 .27500 


-0.24600 


-0.21900 


-0.18500 


-0.15100 


-0.15000 


-25.000 


-0.27*00 


-0.25900 


-0.23900 


-0.21600 


-0.19300 


-0.15000 


-0.14200 


-0.13600 


-20.000 


-0.22S00 


-0.21H0G 


-0.19700 


-0.18100 


-0.16300 


-0.13400 


-0.12300 


-0.12000 


-15.000 


-0.17100 


-0.16100 


-0.14800 


-0.14100 


-0.12800 


-0.10600 


-0 . 1 0000 


-0.100O0 


-10.000 


-0.11500 


-0.10700 


-0.10000 


-0.09500 


-0.09100 


-0.07400 


-0.07300 


-0. 07400 


-5.000 


-0.06000 


-0.05H00 


-O.OHSOO 


-0 . 048OG 


-0.04800 


-0.04200 


-0.04200 


-0.04200 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.05000 


0.04600 


. 04600 


0.04800 


0.05600 


0.05000 


0.04400 


0.04500 


10.000 


0.10100 


0.10000 


0. 09500 


0.10500 


0.12000 


0.11600 


o.cesoo 


0.07800 


15.000 


0.13900 


0.13800 


0.14200 


0.16300 


0.17800 


0.17400 


0.12400 


0.09200 


20.000 


0.16500 


0.17500 


0.18700 


0.22500 


0.2S600 


0.52400 


0. 14200 


O.C?+00 



ENGINEER ^ <a? i 



FIGURE 4. 
ELEVON LIFT 



1.2.1-16 

COEFFICIENT 



INCREMENT 



4.1.2.1-19 



SE72-SI-:-CCec IM 



'1* 



Rockwell International 

SpactOivMton 



MACH NUMBER 



1.300 



DELE CDEGD 

-50 -25 25 

T I | I i i I 1 I i I I j 

I I I i I'l i i i I i 



UJ 

_! 
O 

a 




-so 



-15 



5 

ALPHA CDEGD 



CONFIGURATION 



BASELINE 0R3ITER VEHICLE 
OTTER OF GRAVITY XO » FS 1076.7 IN. 
OR YO - BL 0.0 IN. 

rCHENT REFERENCE 20 - W. 375.0 IN. 



REFERENCE 0IfE>6ION5 
WIN3 AREA SU • 2690.00 SQ.FT. 
WING SPAN 6VI " 78.056 FT. 
M.A.C. CW • 39.560 FT. 

BCOY LENGTH LB - 1590.3 IN. 



ALPHA <C€G) 



•10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



2C.000 



35.000 
H 



OELE (DEO) 



-M0. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ELEVQN LIFT INCREMENT 



-0.38100 
-0.34400 
-0.30300 
-0.25700 
-0.20900 
-0.16000 
-0.I05O0 
-0.05500 
0.0 

0.04400 
0.07700 
0.10500 
0.18900 



-0.30400 
-0.27500 
-0.24500 
-0.20900 
-0.17000 
-0.12500 
-0.08300 
-0.03800 
0.0 

0.04400 
0.08200 
0.12600 
0.16900 



-0.27000 
-0.2H600 
-0.21700 
-0.18600 
-0.15100 
-0.11400 
-0.07500 
-0.03500 
0.0 

0.04000 
0.07800 
0.12300 
0.17600 



-0.25000 
-0.23500 
-0.21500 
-0.18300 
-0.14800 
-0.11300 
-0.07500 
-0.03800 
0.0 

0.04000 
0.08500 
0.13600 
0.19500 



-0.22500 
-0.20500 
-0.18300 
-0.16200 
-0.13400 
-0.10900 
-0.07600 
-0.03800 
0.0 

0.05000 
0.09500 
. 14300 
1B800 



-0.20000 
-0.18500 
-0.16000 
-0.14400 
-0.12300 
-0.09700 
-0.06500 
-0.03500 
0.0 

0.04600 
0.09000 
0.13400 
0.17900 



-0.18000 
-0.17100 
-0.16100 
-0.14700 
-0.13000 
-0.10800 

-o . oeoco 

-0.04100 
0.0 

0.04500 
0.09100 
0.10800 
0.11 900 



-0.16000 
-0.15300 
-0. 14400 
-0.13200 
-0.11800 
-0.09900 
-0.07500 
-0.04000 
0.0 

0.04100 
0.07100 
. 08300 
. C89C0 



EM3IJCER £&> 

DATE... Z3HSI3J. 



FIGURE 4.1.2.1-17 
ELEVQN LIFT COEFFICIENT INCREMENT 



4.1.2.1-2 



SD 



i *- - ■ 



fCCC IM 



#1% 



Rockwell International 

SpacaDvoaon 



MACH NUMBER 



LU 

_l 

8 



-.4 




1 I I I I I ! I I I I 1 I t 1 ' I I I I I I I 1 1 I i I 1 I I I I I I I I I I 1 1 I 

-5 5 10 15 20 25 30 

ALPHA CDEGJ 



CCfF I GlRAT I ON 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO • F5 1075. 7 IN. 
OR YO - BL 0.0 IN. 

«>€NT REFERENCE ZO • UL 375.0 IN. 



REFERENCE OireNSIONS 

WING AREA SW - 2690.00 SQ.FT. 

WIND SPAN 3-1 ■ 78.055 FT. 

M.A.C. CW • 39.560 FT. 

BODY LENGTH LB ■ 1290-3 IN. 











ALPHA 


(DEG) 








- 10.000 


-5.000 


C 


5.000 


I0.C30 


15.000 


20.000 


25.000 


DELE (DEC) 


A 


8 


C 





E 


F 


G 


H 








ELEVCN LIFT 


INCREMENT 








-40.000 


-0.22412 


-0.20786 


-0.22071 


-0.20 12S 


-0.18229 


-0.17347 


-0.1672H 


-0.15511 


-35.000 


-0.20612 


-0.19579 


-0.20103 


-0.16214 


-0.16537 


-0.15911 


-0.15399 


-0.14908 


-30.000 


-0.18422 


-0.17763 


-0.17821 


-0.I6213 


-0.15153 


-0.14892 


-0.13781 


-0.13888 


-55.000 


-0.15860 


-0.15522 


-0.15060 


-0.13S04 


-0.I34M5 


-0.132SS 


-0.12229 


-0.1H375 


-20.000 


-0.13254 


-0.12874 


-0.12353 


-0.11561 


-0.10678 


-0.10852 


-0.10055 


-0.09902 


-15.000 


-0.10205 


-0.09831 


-0.09235 


-0.08915 


-0.08217 


-0.08614 


-0.07853 


-0.07/ AS 


-10.000 


-0.07174 


-0.05635 


-0.06076 


-0.05997 


-0.05485 


-0.05839 


-0.0S275 


-0.05240 


-5.000 


-0.03630 


-0.03255 


-0.03029 


-0.03213 


-0.02575 


-0.02730 


-0.02638 


-0.02565 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.03035 


0.03189 


0.C3005 


0.03109 


0.03508 


0.03976 


0.04369 


0.04748 


10.000 


0.05833 


0.06577 


0.06064 


0.06*20 


0.07350 


0.07889 


0.08717 


0.09579 


15.000 


0.09110 


0.09H15 


0.C8960 


0.09890 


0.10H87 


0.11829 


0.15-71 


0. 14783 


20.000 


0.12382 


0.11766 


0.12316 


0.13760 


0.13502 


0.16007 


0.18199 


0.19600 



ENGINEER £*££_ 



FIGURE 4.1.2.1-18 
ELEVON LIFT COEFFICIENT INCREMENT 



4.3 .2.1-21 



SD72-SH-CC6C IM 



#1* 



Rockwell International 

Spac* Division 



HACH NUMBER = 2.000 

.«♦«-! — r i I i I m I n i i | i i i i I i i i i M ; i M ! i i r 



DELE CDEG) 

-50-25 ^5 

i I : i t • I 



LU 

o 

o 




5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELINE CRBITER CHICLE 
CENTER CF GRAVITY XO ■ FS 1076.7 IN. 
OR YO - a. 0-0 IN. 

MCftNT REFERENCE ZO - WL 375.0 IN. 



IN 

REFERENCE OlfCNSICNS 




WING AREA SW - 2690.00 


SQ.FT. 


WING SPAN 8W » 78.056 


FT. 


M.A.C. CW - 39.560 


FT. 


BCCY LENGTH LB » 1290.3 


IN. 



DELE tOEG) 



-40 . 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



ALPHA (DEO 



-10 300 
A 



-5.000 
B 



0.0 
C 



5.000 | 




10.000 
E 



15.000 

F 



20.000 
G 



55.000 
H 



30.000 
I 



ELEVCM LIFT INCREFCNT 



-0.12500 
-0.12000 
-0.11000 
-0.09700 
-0.08700 
-0.06900 
-0.04700 
-0.02H00 
0.0 

0. 01900 
0.03900 
0.059O0 
0.07900 



-0.12000 
-0.11500 
-0.10600 
-0.09700 
-0.08500 
-0.06800 
-0.04700 
-0. 024 00 
0.0 

0.02100 
0.04200 
0.06100 
Q. 07800 



-0.11500 
-0.11000 
-0.10300 
-0.09300 
-0.08100 
-0.06000 
-0.04000 
-0.02000 
0.0 

0.01900 
0.03900 
0.05900 
0.07800 



-0.10500 
-0 . 09500 
-0.08700 
-0.07700 
-0.07000 
-0.05300 
-0.03500 
-0.02000 
0.0 

0.01900 
0.03900 
0. 05900 
C. 08200 



-0.10000 
-0.09400 
-0.085O0 
-0.07600 
-0.06700 
-0.05200 
-0.03700 
-0.01900 
0.0 

0.02000 
0.04400 
0.05100 
. 08700 



-0.10200 
-0.09800 
-0.09000 
-0.08300 
-0.06800 
-0.05200 
-0.03700 
-0 . 02000 
0.0 

0.02200 
0.04200 
0.06500 
0.09000 





-0.10500 


-0.10500 


-0 . 1 0500 


-0.10300 


-0.09800 


-0 . 09800 


-0.09300 


-0.08700 


-0.08900 


-0.07900 


-0.07700 


-0.07900 


-0.06500 


-0 . 06600 


-0.06500 


-0.05000 


-0 . 05000 


-0.05000 


-0.03500 


-0.03500 


-0 . 03500 


-0'. 01900 


-0.01900 


-0.01900 


0.0 


0.0 


0.0 


0.02200 


. 02200 


0.02200 


0.04300 


0.0^700 


. 04700 


0.06700 


0.07200 


. 07?00 


0.09803 


0.10000 


c. :oooo 



ENGINEER S<35 
DATE '§J7ij.2f 



FIGURE 4.1.2.1-19 
P FVftN LIFT COEFFICIENT INCREMENT 



4.1.2.1-2 2 



SD"/2 



-CCVC IM 



€> 



Rockwell International 

Spec* Division 



J 



MACH NUMBER 



3. 000 



dele cdeg: 

-50 -25 25 



1 t I I i I i ! i i i i 



UJ 

_j 

8 



** [ I I i I I I I i I I I I I T I i i M I I I I I l~T 



i i 1 i i i i I i i i : I i i 



: ^J^^^^ 



^&7*ett.*g&S$L '^^^^i^^^Sj^^^-^^^^fr^^ 



-.6 



I I I I 



J_L 



I I 1 I. -L 



'^M* 



i I i i I 1 I I 1 1 I 



I. i i I I I 



-20 



-15 



-10 



5 10 

ALPHA 'DEGD 



15 



20 



CONFIOJRATIJN 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO ■ FS 1076.7 IN. 

OR YD - B. 0.0 IN. 

rCrtHT REFERENCE ZO - UL 375.0 IN. 



JN 

REFERENCE DlrENSI0N5 




WING AREA SU - 2690.00 


SC.FT. 


WING SPAN BW » 78.056 


FT. 


M.A.C. CW » 39.560 


FT. 


BCOY LENGTH LB « 1290.3 


IN. 



DELE (PEG) 



ALPHA 10EG) 



-10.000 
A 



-5.000 
8 



0.0 
C 



5.000 
D 



10.000 

E 



15.000 

F 



20.000 
G 



ELEVCN LIFT INCREMENT 



-40.000 

-35.000 

-30.000 

-25.000 

-50.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



-0.09500 
-0.08800 
-0.08200 
-0.07200 
-0.05900 
-0.04400 
-0.02700 
-0.01500 
0.0 

0.009O0 
0.01500 
0.02200 
0.02500 



-0.08500 
-0.08000 
-0.06700 
-0.05900 
-0.05000 
-0.04000 
-0. 02700 
-0.01400 
.0 

.00900 
.02000 
.02500 



0.03200 



-0.07000 
-0.06000 
-0.05200 
-0.04500 
-0.03700 
-0.02700 
-0.01700 
-0.01000 
0.0 

0.00900 
. 02200 
0.03400 
. 04500 



-0.06300 
-0.05500 
-0.04800 
-0.04200 
-0.03500 
-O.C.^00 
-0.0.700 
-0.01000 
0.0 

0.01000 
0.02200 
0.03600 
0.05200 



-0.06000 
-0.05500 
-0.04800 
-0.04000 
-0.03500 
-0.02700 
-0.02000 
-0.01100 
0.0 

0.01400 
0.02300 
. 04200 

. osooo 



-0.06800 
-0.06000 
-0.05100 
-0.04*300 
-0.03400 
-0.02S00 
-0.02100 
-0.01200 
0.0 

0.01500 
0.02900 
. 04900 
0.06800 



-0.06500 
-0.05800 
-0 . 05300 
-0 . 04800 
-0.04100 
-0.03300 
-0.02200 
-0.01300 
0.0 

0.01500 
0.03500 
0.05500 
. 07500 



ENDINEER.^^- 
OATE_g&gZZ^- 



FIGURE 

EL E VON L 



4.1.2.1-20 

TFT COEFFICIENT 



! NCREMENT 



.1.1 i t. 



30 



25.000 
H 



-0.07400 
-0.06600 
-0.05800 
-0.05000 
-0.04200 
-0.03200 
-0.02100 
-0.011.00 
0.0 

C. 01800 
. 03500 
0.05800 
. 08000 



4.1.2.1-2: 



*? P "i o o 



CCCC IM 



* 



Rockwell International 

Space Division 



MACH NUMBER 



3.000 



DELE CDEG] 

-50 -25 25 

j I I I I | I I I | I I ! ! ( 

i i i i I i m r~n n r~r~ i r 



_1 

a 




30 

CDEG 3 



COFIGURATION 



BASELINE CR61TER VEHICLE 
CENTEF OF GRAVITY XO - FS 1076.7 IN. 
OR YO • BL 0.0 IN. 

r-CTtNT REFERENCE ZO =■ WL 375.0 IN. 



REFERENCE DlfENSIONS 
WIKG AREA SW - 2690.00 SQ.FT. 
WING SPAN BUI » 78.056 FT. 
M.A.C. CW - 39.560 FT. 

B0OY LENGTH LB - 1290.3 IN. 



ENGINEER Qf^^. 





ALPHA (C€G) 






15.000 


20.000 


25.000 


30.000 


35.000 


HO. 000 


H5.000 


OGLE (DEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVON 


LIFT INCREl 


*€NT 






-HO. 000 


-0.06800 


-0.06500 


-0.07H00 


-0.08200 


-0.08850 


-0.09500 


-0.10225 


-35.000 


-0.06000 


-0.05800 


-0.06600 


-0.07500 


-0.08150 


-0.08800 


-0.09500 


-30.000 


-0.05100 


-0.05300 


-0.05800 


-0.06700 


-0.07H00 


-0.08100 


-0.08837 


-25.000 


-0. OH 300 


-0.0H800 


-0.05000 


-0.06000 


-0.06722 


-0.07HOO 


-0.08062 


-20.000 


-0.03HOO 


-0.0H100 


-O.OH200 


-0.05200 


-0.06029 


-0.06700 


-0.07225 


-15.000 


-0.02900 


-0.03300 


-0.03200 


-0.03900 


-0.0H700 


-0.05500 


-0.05962 


-10.000 


-0.02100 


-0.02200 


-0.02100 


-0.02600 


-0.03150 


-0.03700 


-0.OH137 


-5.000 


-0.01200 


-0.01300 


-0.01100 


-0.01300 


-0.01500 


-0.01700 


-0.01900 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01500 


0.0)500 


0.01800 


0.02100 


0.02177 


0.02100 


0.01912 


10.000 


0.02900 


0.03500 


0.03500 


O.OH200 


0.0H3S3 


O.OH200 


O.CiVbO 


15.000 


0.0H9OO 


0.05500 


0.05800 


0.07200 


0.07HS2 


0.07200 


0.06563 


20.000 


. 06800 


0.07500 


0.08000 


0.10300 


0.10601 


0.10300 


0.09737 



FIGURE 4.1.2.1-21 
Ft FVflN LIFT COEFFICIENT INCREMENT 



4.1.2.1 



S'C 7 Z 



cere ! .vi 



#> 



Rockwell International 

Spac* Divwon 



J' 



MACH NUMBER 



.4- 



UJ 

_J 
u 

o 




I I I I I I I I 1 ! I ! 1 I I I I 1 I I I I I I I I I I I I I i 

-5 5 10 15 20 

ALPHA CDEG) 



CONFIGURATION 



BASELINE CRB1TER VEHICLE 

CENTER Of GRAVITY XO - F5 1076.7 IN. 

OR YO - 8L 0.0 IN. 

MO-ENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE Olt-ENSIGNS 
WIND AREA SW - 2690.00 SQ.FT. 
V.IN3 SPAN SU - 79.055 FT. 
h.A.C. CW - 39.550 FT. 

9COY LENGTH LB ■ 1290.3 IN, 



DELE (PEG) 



-40.000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.00C 

0.0 

5.000 

10.000 

15.000 

20.00C 



ALPHA (PEG) 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 
D 



10.000 
E 



15.000 

F 



20.000 

G 



25. 000 
H 



ELEVON LIFT INCRErENT 



08900 

08500 

07900 

07000 

06000 

,04900 

•0.03500 

■0.02000 

0.0 

0.00800 
G. 01100 
0.01100 
0.01000 



-0.07300 
-0.06600 
-0.05900 
-0 . 05200 
-0.04500 
-0.03HOO 
-0.02300 
-0.01100 
0.0 

0.00700 
0.01400 
. 02000 
0.02600 



-0.06000 
-0.05500 
-0.05000 
-0.04300 
-0.03600 
-0.02800 
-0.02000 
-0.01200 
0.0 

. 00800 
0.01500 
0.02400 
. 03800 



-0.05100 
-0.04500 
-0.04000 
-0.03400 
-0.02900 
-0.02100 
-0.01400 
-0.00700 
0.0 

0.01000 
0.02100 
0.03500 
0.05000 



-0.04300 
-0.03900 
-0.03400 
-0.02900 
-0.02600 
-0.02000 
-0.01500 
-0.00800 
0.0 

0.01200 
0.02200 
0.03900 
. 05900 



-0 . 04700 
-0.04100 
-0.03500 
-0.02900 
-0.02300 
-0.01700 
-0.01200 
-0.00500 
0.0 

0.01400 
0.02900 
0.05000 
C.07100 



-0.05100 
-0.04500 
-0.03S00 
-0.02900 
-0.02400 
-0.01700 
-0.01100 
-0.00500 
0.0 

0.01400 
0.03000 
0.05400 
0.08200 



-0.06000 
-0.05300 
-0.04500 
-0.03800 
-0.03100 
-0.02300 
-0.01500 
-0.00800 
0.0 

0.01900 
0.03800 
0.06200 
. 08700 



ENGINEER J££L 



FIGURE 
ELEVON L 



4.1.2.1- 

IFT COEFF 



22 

ICIENT 



INCREMENT 



4.1.2 1-25 



SD"/2 



SH 



oceo im 



#1* 



Rockwell International 

SpacaDivsaon 



MACH NUMBER 



4.000 



-50 



DELE COEG) 

-25 25 



a 



.0 



-.2 



-.4 



i ; i i 



I I I I I I i i i I i i i 




-. 6 1 1 1 1 l 



iii i 



TT 



! I I 



! I 



1 ' ' ' 1 I I I 1 1 1 1 



I I I I 1 I I i 



1 I I 



10 



15 



20 



25 30 

ALPHA CDEGD 



35 



40 



45 



50 



CONFIGURATION 




BASELINE ORB1TER VEHICLE 


REFERENCE DIMENSIONS 




CENTER OF GRA.'ITY XO • FS 1076.7 IN. 


WING AREA SM - 2690.00 


SO. FT. 


OR Y0 - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOENT REFERECE 20 - H. 375.0 IN. 


M.A.C. CW ■ 39-550 


FT. 




BODY LENGTH LB - 1290.3 


IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


-t5.000 


DELE (DEG) 


F 


G 


H 


I 


J 


K 


L 






ELEVON 


LIFT INCRE 


^€NT 






-40 . 000 


-0. OH 700 


-0.05100 


-0.06000 


-0.D70O0 


-0.07700 


-0.08400 


-0.09212 


-35 . 000 


-o.cmioo 


-0.04500 


-0.05300 


-0 . 06500 


-0.07300 


-0.08100 


-0.C8937 


-30 . 000 


-0.03500 


-0.03600 


-0.04500 


-0.05900 


-0.06650 


-0.07400 


-0.08187 


-25.000 


-0.02900 


-0.02900 


-0.03800 


-0.05100 


-0.05850 


-0.06600 


-0.07387 


-20.000 


-0 . 02300 


-0.02400 


-0.03100 


-0.04300 


-0.05000 


-0.05700 


-O.C6400 


-15.000 


-0.01700 


-0.01700 


-0.02300 


-0.03500 


-0.04050 


-0.04600 


-0.05187 


-10. COO 


-0.01200 


-0.01100 


-0.01500 


-0.02500 


-0.02900 


-0.03200 


-0.03650 


-5.000 


-0.00600 


-0.00500 


-0.00800 


-0.01500 


-0.01650 


-0.01SOO 


-0.01950 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01400 


0.01400 


0.01900 


0.01900 


0.01900 


0.01900 


0.01712 


10.000 


. 02900 


0.03000 


0.03800 


0.04100 


0.04216 


0.04100 


0.03668 


15.000 


. 05000 


0.05400 


0.06200 


. 05600 


0.06767 


. 06600 


C. 05925 


20 . 000 


0.07100 


0.0S200 


. OS700 


. 09200 


0.09426 


. 09200 


0.08150 



ENGINEER 
0AT£_.Sl'M.7£. 



FIGURE 4. 
ElEVON LIFT 



1.2. 1-23 
COEFFICIENT INCREMENT 



4.1.2.1-26 



S G 1 



CC 1 



PM Rockwell International 
^ SpacaDMtfon 



Jf 



K 



MACH NUMBER 



5.000 



DELE COEG: 
-50 -25 25 

f I I I i | I I I I | I I I 
i I i I I I I I 



UJ 

_i 
C_J 

o 




-.4 



ALPHA CDEGD 



OflCURATICN 



BASELINE 0R81TER VEHICLE 

CENTER OF GRAV:TY XO ■ FS I07S.7 IN. 

OR YO • BL 0.0 IN. 

MGtENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE DIC6}SICN5 
WING AREA SW - 2690.00 SQ.FT. 
WIND SPAN BW - 78.056 FT. 
H.A.C. CW - 39.560 FT. 

amy length lB » 1590.7 in. 



C€LE (C€0> 



-40.000 

-35.000 

-30.000 

-85.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.0C3 



-10.000 
A 



-5 000 
B 



0.0 
C 



ALPHA tDEG) 
5.000 




10.000 
E 



Fl FVON LIFT INCRETENT 



15.000 

F 



20 . 000 
G 



25000 
H 



-0.06500 
-0.05900 
-0.05200 
-0.04600 
-0.04000 
-0 . 03000 
.02400 
.01300 
.0 

.00500 
0.005)0 
0.00700 
0.00200 



-0. 
-0. 

0. 

0. 



-0.05700 
-0.05100 
-0.04500 
-0.04000 
-0.03400 
-0.02S00 
-0.01700 
-0.00900 
0.0 

. 00600 
0. 01200 
0.01300 
0.01^00 



-0.04800 
-0.04500 
-0.03800 
-0.03300 
-0.02800 
-0.02100 
-0.01400 
-0.00700 
0.0 

0.00700 
0.01400 
0.01900 
0.02400 



-0.04200 
-0.03800 
-0 . 03400 
-0.02900 
-0.02500 
-0.01900 
-0.01300 
-0.00500 
0.0 

0.00900 
0.01B00 
0.02900 
O.C3900 



-0.03600 
-0. 034 00 
-0.02900 
--0. 02600 
-0.02200 
-0.01700 
-0.01600 



-0 








00500 
,0 

.01100 
.02200 
.03300 
.05100 



-0.04000 
-0.03600 
-0.03200 
-0.02800 
-0.02400 
-0.01800 
-0.01200 
-O. 00600 
0.0 

0.01300 
0.02500 
0.04800 
0.07000 



-0.04500 
-0.04000 
-0.03500 
-0.03000 
-0 . 02500 
-0.01900 
-0.01700 
-0.00500 
0.0 

0.01700 
0.02300 
0.05300 
0.05700 



-0 . 05500 
-0 . 04900 

-0.04HOO 

-O.C3800 
-0.03300 
-0.02500 
-0.01600 
-0 . 00300 
0.0 

0.01950 
0.03460 
0.05900 
0.08700 



ENGINEER O^Z.-- 
DA7Z._?Jj2jL2J. 



F'.GURE 
ELEVONU 



4.1.2.1-24 

FT COEFFICIENT 



INCREMENT 



U. 1.2. 1-27 



SD 



°-SH 



/<£. 



c'cec im 



#J* 



Rockwell International 

Spec* Diviacw 



MACH NUMBER 



5. 000 



i i I i i i i I i i i l I l I I i 



M DELE CDEGD 
- so -as o 

I I i r 



.2 



■ Or 



n--J^' 



I 1 I I I 






TTT 



T-r 



35^ 



i I i i 



I i I 



T ill 



^Eiji^l 



UJ 

_J 

8 




-.4 



-.6^Li_L 



10 



"' ' ! ' ' [ ' ' ' '' " I I 1 i m i h i nl M || 



15 



20 25 30 35 

ALPHA CDEGD 



40 



45 



I I I I I I | 
50 55 



CONFIGURATION 



BASELINE 0R91TER VEHICLE 

CENTER OF GRAVITY XO » FS S07S." 7 IN. 

OR YO ■ BL " 0.0 IN. 

MOMENT REFERENCE ZO - M. 375.0 IN. 



REFERENCE C!^ENSI0N5 
WIND AREA SW • 2690.00 SQ.FT. 
WING SPAN BUI « 78.056 FT. 
M.A.C. CA - 39.550 FT. 

BCOY LENGTH LB ■ 1290. J IN. 











ALPHA 


ICEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (CEG) 


F 


G 


H 


I 


J 


K 


L 


M 








ELEVON LIFT 


INCRETENT 






-40.000 


-0.04000 


-0.04500 


-0.05500 


-0.06500 


-0.07500 


-0.06500 


-0.09312 


-0.10000 


-35.000 


-0.03500 


-0.04000 


-0.04900 


-0.05900 


-0.06870 


-0.07800 


-0.08675 


-0.09500 


-30.000 


-0.03200 


-0.03500 


-0.04400 


-0.05300 


-0.05250 


-0.07200 


-0.08038 


-0.08800 


-25.000 


-0.02900 


-0.03000 


-0 . 03800 


-0.04600 


-0.05550 


-0.06500 


-0 . 07300 


-0 . 08000 


-20.000 


-0.02400 


-0.02500 


-0.03300 


-0 . 04000 


-0.04850 


-0.05700 


-0.06400 


-0.07000 


-15.000 


-0.01B00 


-0.01900 


-0.0250C 


-0.03000 


-0.03700 


-0.04400 


-0.05100 


-0.05800 


-10.000 


-0.01200 


-0. 01700 


-0.01600 


-0 . 02400 


-0.03002 


-0. 03500 


-0 . 03937 


-0.04300 


-5.000 


-0 . 00600 


-0.00500 


-0.00800 


-0.01300 


-0.01621 


-o.oieoo 


-0.01862 


-0.01800 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01300 


0.01700 


0.01950 


0.02200 


0.02262 


0.02200 


0.02050 


0.0 1 SCO 


10.000 


0.02500 


0.02B00 


0.03460 


0.04120 


0.04235 


0.04120 


0.03887 


0.03500 


15.000 


0.04800 


0.05300 


0.05900 


0.06200 


0.06330 


0.06200 


0.05537 


0.04700 


20.000 


0.07000 


0.08700 


. 08700 


0.08700 


0.08494 


o.oeooo 


0.C7087 


o.osaro 



ENGINEER p^£__ 
PATE__'ZZI3 l Zfg! 



FIGURE 4.1.2.1-25 

ELEVON LIFT COEFFICIENT INCRFHrNT 



4.1.2.1-2 1 



SD 7: 



v. >. V I ,vl 



'1* 



Rockwell International 

SpacaDMMon 



jr- 



MACH NUMBER 



8.000 



DELE CDECO 

-50-25 _25 



TTT 



I I i l i 



.2 



Q 



•** n i i i I i i i ■ t ' ' i i I t 






V**' 



TTT 



-.4 



-.6 




l I I 



1 I I I I I I I I I I I I I 



i i I I I 1 






'''' 



-20 



-15 



■10 



I M ' ' ' ' ' 
-5 5 



i 1 



10 



llll I I | || " I I III 

15 20 25 30 



ALPHA CDEG) 



COF1GURAT10N 



BASELINE CRBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1075.7 IN. 
OR YO • BL 0.0 IN. 

MH-ENT REFERENCE ZO - U. 375.0 IN. 



L 



REFERENCE DIf€NS!CN5 




WING AREA 


sw ■ 


2530.00 SQ.FT. 


WIND SPAN 


BW • 


78.056 


FT. 


M.A.C. 


CW - 


39.560 


rr. 


BODY LENGTH LB - 


1290.3 


IN. 



ALPHA (C£G) 



DELE (PEG) 



-40.000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



•10.000 
A 



-5.000 
B 



0.0 
C 



-0.06900 
-0.05B00 
-0.04700 
-0.03900 
-0.03100 
-0.02300 
-0.01500 
-0.00700 
0.0 

0.00500 
0.01000 
0.01000 
0.01100 



5.000 10.000 

D I E 

rirvftt LIFT INCREMENT 



15.000 
F 



20.000 
G 



25.000 

H 



-0.05500 
-0.0M800 
-0.04000 
-0.03300 
-0.02700 
-0.02100 
-0.0 1400 
-0 . 00700 
0.0 

0.00500 
0.01000 
0.01000 
0.01 100 



-0. 

-0. 

-0. 

-0. 

-0. 

-0. 

-0, 

-0 








04200 
.03700 
. 03300 
.02900 
. 02300 
.01900 
.01200 
.00700 
.0 

.00500 
.01000 
.01000 
.01100 



-0.03300 
-0.03100 
-0.02900 
-0.02500 
-0.02200 
-0.01900 
-0.01500 
-0.00700 
0.0 

0.00700 
0.01400 
0.02200 
. 02900 



-0.02500 
-0.02400 
-0 . 02400 
-0.02200 
-0.02000 
-0.01800 
-0.01500 
-0.01 000 
0.0 

. 00900 
0.01700 
. C2900 
. 0H600 



-0.03000 
-0.02800 
-0.02700 
-0.02500 
-0.02300 
-0 . 02000 
-0.01700 
-0.00800 
0.0 

0.01200 
0.02400 
. 04000 
. 05700 



-0.03400 
-0 . 03200 
-0.03100 
-0.02800 
-0.02500 
-0.02200 
-0.01800 
-0.01200 
0.0 

0.01400 
0.02900 
C . 04000 
. C5700 



-0 . 04400 
-0.04200 
-0.03900 
-0.03600 
-0.03300 
-0.02800 
-0.02300 
-0.01200 
0.0 

0.01700 
0.03500 
0.C54O0 
0.07300 



ENGINEER JS^O 
OATE_J?7/3/?^ r 



FIGURE 4. 
Ft.EVON LIFT 



1.2.1- 26 

COEFFICIENT 



INCREMENT 



4.1.2.1-29 



SC72-SK--CCCO 1M 



#JI 



Rockwell International 

Space Division 



MACH NUMBER 



_l 
O 
O 



-.2 



-.6 



I I I I I l I I I 



8.000 
I l I i I l 



DELE CQEG) 

-50 -55 



ii i 



^^^^^^^dz^—^^^^^^. 



''■'I 

Mil 



i — r 



I ! I I I I I 



^^ : ?s*^®^^^^^^^^i 



B^^~ 



imi 



I I I I I i I ! I I I I I 



I I I I I 



10 15 20 25 30 35 

ALPHA CDEG3 



40 



45 



50 



OFI0URATI0N 




BASELINE 0R8ITER VEHICLE 


REFERENCE Qlf-ENSIONS 




CENTER OF GRAVITY XO » FS 1075.7 IN. 


WING AREA SW » 2690.00 


SQ.FT. 


OR YO • a. 0.0 IN. 


WING SPAN 3W - 78.056 


FT. 


fOtNT REFERENCE 20 • W. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BOOY LENGTH LB • 1290.3 


IN. 











ALPHA 


(DIG! 








15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELE (CCO 


F 


G 


H 


I 


J 


K 


L 


M 








ELEVEN LIFT 


INCREMENT 








-40.000 


-0.03000 


-0.03400 


-0.04400 


-0.05400 


-0 . 05500 


-0.07600 


-0.08537 


-0.09500 


-35.000 


-0.02800 


-0.03200 


-0.04200 


-0.05100 


-0.06200 


-0.07300 


-0.08212 


-0 . 09000 


-30.000 


-0.02700 


-0.03100 


-0 . 03900 


-0.04800 


-0.C5900 


-0.07000 


-0.07875 


-0.08500 


-25.000 


-0.02500 


-0.02900 


-0.03600 


-0 . 04400 


-0.05350 


-0.06300 


-0 . 07063 


-0 . 07700 


-20.000 


-0.02300 


-0.02500 


-0.03300 


-0 . 04000 


-0.04800 


-0.05600 


-0 . 05287 


-0.06900 


-15.000 


-0.02000 


-0.02200 


-0.02800 


-0.03400 


-0.03950 


-0.04500 


-0.050S8 


-0.05700 


-10.000 


-0.01700 


-0.01300 


-0 . 02300 


-0 . 02900 


-0 . 03050 


-0.03300 


-0.03587 


-0.03900 


-5.000 


-0.00800 


-0.01200 


-0.01200 


-0.01700 


-0.01750 


-0.01800 


-0.01850 


-0.01900 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01200 


0.01400 


0.01700 


0.02100 


0.02150 


0.02000 


0.01725 


0.01300 


10.000 


0.02400 


0.02800 


0.03500 


0.04100 


. 04300 


0.04100 


. 03500 


. 02500 


15.000 


0.04000 


. 04800 


0.05*00 


0.06000 


0.06240 


0.06000 


0.05100 


0.03600 


20.000 


0.05700 


. 05700 


. 07300 


. 07900 


0.08186 


. 07900 


0.06400 


. 03900 






ENGINEER 

DATE 5jl3i22. 



FIGURE 
ELEVON L 



4. 1.2.1- 

IFT C0EFF 



27 
ICIEN1 



INCRE^ENl 



U. 1.2. 1-30 



Si: 



-tv. 



'1* 



Rockwell International 

Spac* Division 



j: 



MACH NUMBER 



10.000 



.0 



UJ 

8 



TIM i 



Fi 1 I I I I I I i I I I I i I 



DELE CDEGD 

-50 -25 25 

[•1 I I I |- I I I I | I I I 

■Till TTT 



T Illi 




-.4 



-.6 



I ' M I 1 



'^^^-^t^^^Xm^S^^*^ 'I' I 



-eo 



-15 



-10 



| | I I I M I ' ' I I I I I I I M I M 
5 10 15 20 



ALPHA CDEGD 



CONFIGURATION 



BASELINE CRB1TER VEHICLE 

CENTER Cf GRAVITY XD - F5 1075.7 IN. 

OR YO • BL 0.0 IN. 

MO-ENT REFERENCE ZO ■ M. 375.0 IN. 



)N 

REFERENCE DirENSICNS 




WING AREA SW ■ 2590.00 


SQ.FT. 


WING SPAN BW - 78.056 


FT. 


M.A.C. CW - 39.550 


FT. 


BODY LENGTH LB - 1290.3 


IN. 



DELE (PEG) 



ALPHA i PEG) 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
D 



I C . 000 

E 



15.000 

F 



-40.000 
-35.000 
-30.000 
-25.000 
-20.000 
-15.000 
-10.000 



-5 


5 



000 



000 
10.000 
15.000 
20.000 



ELEVON LIFT INCRErgNT 



20 . 000 
G 



-0.07000 
-0.05900 
-0.04900 
-0.03900 
-0.02900 
-0.02200 
-0.01400 
-0. 00700 
0.0 

0.00400 
0.00900 
0.01000 
0.01100 



-0.05600 
-0.04800 
-0.04100 
-0.03300 
-0.02600 
-0.01900 
-0.013O0 
-0.00600 
0.0 

0.00400 
0.00900 
0.01000 
0.01100 



-0.04200 
-0.03700 
-0.03200 
-0.02800 
-0.02300 
-0.01700 
-0.01100 
-0 . 00600 
0.0 

0.00400 
0.00900 
0.01000 
0.01000 



-0.03300 
-0.03000 
-0.02700 
-0.02400 
-0.02100 
-0.01500 
-0.01000 
-0.00500 
0.0 

. 00700 
0.01300 
0.02000 
. 02600 



-0.02500 
-0.02400 
-0.02200 
-0.02000- 
-0.01800 
-0.01400 
-0.00900 
-0.00500 
0.0 

0.00800 
0.01700 
0.03100 
. 04500 



-0.03000 
-0.02800 
-0.02600 
-0.02400 
-0.02200 
-0.01500 
-0.01100 
-0.00500 
0.0 

0.01100 
0.02200 
0.03900 
0.05600 



-0.03400 
-0.03200 
-0.03000 
-0.02800 
-0.02600 
-0.01900 
-0.01300 
-0.00500 


0.01400 
0.C2900 
0.04300 
. 06700 



ENG 
DATE 



FIGURE 
ELEVON L 



4.1.2.1- 

1FT COEFF 



28 

ICIENT 



INCREMENT 



MM! 



30 



25.000 
H 



-0 . 04400 
-0.04100 
-0.03800 
-0.03500 
-0.03300 
-0.02500 
-0.01600 
-0.00800 
0.0 

0.01700 
0.03400 
0.05300 
0.07300 



4.1.2.1-31 



SE72-SH-OCCC 1M 



0$ 



Rockwell International 

Space Division 



MACH NUMBER 



1C.000 



DELE CDEG) 

-50-25 25 



I i i i i i i i I r 



.0 



UJ 

_J 
o 
o 



r i i 



i ~ 



r~n — r 



i i i i i i 




-.4 



-.6 



I I 1 I I I ! 



MM 



J,l i. 



i II I '. I 



till i 



10 15 20 25 30 35 

ALPHA CDEG) 



40 



45 



50 



CONF I GURATION 




BASELINE CR9ITER VEHICLE 


REFERENCE DI^NSIONS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU • 78.056 


FT. 


MOrENT REFERENCE ZO « WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY UE'-JGTH LB - 1290.3 


IN. 











ALPHA 


I DEO) 








15.000 


20.000 


25.000 


30 . 000 


35.000 


40.000 


45.000 


50.000 


XLE (DEG) 


F 


G 


H 


I 


J 


K 


L 


M 








ELEVON LIFT 


|^CRE^•ENT 








-HO. 000 


-0.03000 


-0.03400 


-0 . 04400 


-0.05300 


-0.06500 


-0.07700 


-0.08675 


-0.09500 


-35.000 


-0.02800 


-0.03200 


-0.04100 


-0 . 05000 


-0.06100 


-0.07200 


-0 . 08075 


-0 . 08800 


-30.000 


-0.02600 


-0.03000 


-0.03800 


-0.04500 


-0.05600 


-0.06600 


-0 . 07450 


-0.08200 


-25.000 


-0. 02400 


-0 . 02800 


-0.03500 


-0.04300 


-0.052C0 


-0.06100 


-0.06850 


-0.07500 


-20.000 


-0.02200 


-0 . 02500 


-0.03300 


-0.04000 


-D. 04 750 


-0.05500 


-0.05175 


-0.06800 


-15.000 


-0.01600 


-0.01900 


-0.02500 


-0.03000 


-0.03600 


-0.04200 


-0 . 04687 


-0.05100 


-10.000 


-0.01 100 


-0.01300 


-0.01500 


-0 . 02000 


-0.02400 


-0.02800 


-0.03125 


-0.03430 


-5.000 


-0 . 00500 


-0.00600 


-0.00800 


-O.OiOOO 


-C. 01200 


-0.01400 


-0.01562 


-0.01 700 


O.C 


0.0 


0.0 


0.0 


0.0 


:.o 


0.0 


0.0 


0.0 


5.000 


o.ouoo 


0.0140C 


o.onoo 


0.02000 


0.02086 


0.02000 


0.01775 


0.01400 


10.000 


0.02200 


0.02800 


0.03400 


0.04000 


0.04171 


0.04000 


0.03550 


. 02S30 


15.000 


0.03900 


. 0H800 


. 05300 


0.05900 


0.06140 


0.05900 


0.05000 


0.03500 


20 . 000 


. 05600 


. 05700 


0.07300 


. 07900 


0.08188 


0.07300 


C. . 0636c 


0.03??? 



ENGINEER &G? 

QATE__.5ZMZzg 



FIGURE 
ELEVON LI 



4. 1.2. 1-29 

-T COEFFICIENT 



IN"RI M ENT 



k.l.2.1-22 



SD 



1 ■ i :-; •■ C ■ . l C I M 



* 



Rockwell International 

SpacaOvMon 



Ju 



MACH NUMBER 



15.000 



-50 



DELE 

-25 

TTT 



CDEGD 

25 

i i i r | 



Id 

_) 

8 



(III 



.0 



-.2 



-.4 



-.6 



I I I I I 



TTT 



TT 



I II I 



- ^^S^^, 



i i i i I t i i i I i i 



I l 1 l 






TT 



TTT 



-20 



-15 



-10 



i I I I I i I i I I i I I I I I I I I I I 1 I I I 1, 
5 10 15 20 25 30 



ALPHA CDEG) 



CCtsFIGLRATICN 



BASELINE CRB1TER VEHICLE 
CENTER CF GRAVITY X0 - F5 1076.7 IN. 
CR Y0 ■ 8L 0.0 IN. 

M0KENT REFERENCE 20 - W. 375.0 IN. 



REFERENCE DINENSICtS 
WING AREA SW - 2690.00 
WING SPAN BW - 78.055 
M.4.C. CW • 39.550 

8Cl>Y LENGTH LB - 1290.3 



SQ.FT. 
FT. 
FT. 
IN. 











ALPHA 


iceo) 








-10.000 


-5.000 


0.0 


5.0C0 


10.000 


15.000 


20.000 


25.000 


DELE <DEG) 


A 


B 


c 





E 


F 


G 


H 








ELEVON LIFT 


INCRENtNT 








-HO. 000 


-0.07000 


-0.05500 


-0.0H200 


-0.03300 


-0.02500 


-0.03000 


-0.03400 


-0.04400 


-35.000 


-0.05900 


-0.04800 


-0.03700 


-0.03000 


-0.02400 


-0.02800 


-0.03200 


-0 . 04 1 00 


-30.000 


-0.04900 


-0.04100 


-0.03200 


-0.02700 


-0.02200 


-0.02600 


-0 . 03000 


-0.03800 


-25.000 


-0.03900 


-0.03300 


-O. 02800 


-Tj. 02400 


-0 . 02000 


-0.02400 


-0.02800 


-0.03500 


-20.000 


-0.02900 


-0.02500 


-0.02300 


-0.02100 


-0.01B00 


-0.02200 


-0.02500 


-0.03300 


-15.000 


-0.02200 


-0.01900 


-0.01700 


-0.01500 


-0.01400 


-0.01600 


-0.01900 


-0.02500 


-10.000 


-0. 01*400 


-0.01300 


-0.01100 


-0.01000 


-0.00900 


-0.01100 


-0.01300 


-0.01600 


-5.000 


-O. 00700 


-0.00600 


-0.00600 


-0.00500 


-0.00500 


-0.00500 


-O.OOSOO 


-0.00800 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0,0 


0.0 


5.000 


0.0CH00 


0.00400 


0.00400 


0.00700 


0.00800 


0.01100 


0.Q1400 


0.01700 


10.000 


0.00900 


0.00900 


0.0O900 


0.01300 


0.01700 


0.02200 


0.02800 


0.03400 


15.000 


0.01000 


0.01000 


0.0 1000 


0.0200C 


0.03100 


0.03900 


. 0H800 


0.05300 


20.000 


0.01100 


0.01100 


0.01000 


0.02801' 


. 04500 


. C55C0 


0.06700 


0.07^'C 



ENGINEER &Z0 



FIGURE 
ELEv'QN L 



4.1.2.1- 

IFTCOEFF 



30 
IC1EN' 



INCREMENT 



4.1.2.1-33 



SD 



72 -SH 



CCCC 1M 



Jgt 



Rockwell International 

Spaca Division 



MACH NUMBER 
M <- M I ! I I i I I I I 



15.000 



DELE CDEGD 

-50 -25 



25 



.a 



UJ 

_J 
Q 



-.4 



! I I i I I M I I [I : i I I I I ! 




, e l i i nl i ii i hi 



mm r 



— -j^^rC^r' 



^S5: 



■p.--**" 



J—L. 



I I 1 I II I I I I I M I 



LJ ill! 



10 15 20 25 30 35 

ALPHA CDEGD 



HO 



-«45 



50 



O>FlGURATI0N 




BASELINE GRSITER VEHICLE 


REFERENCE DlrOSIIONS 




CENTER OF GRAVITY XO - FS I07S.7 IN. 


WING AREA SW • 2690.00 


SQ.FT. 


OR YO • BL 0.0 IN. 


WING SPAN Bw - 78.056 


FT. 


MOtNT REFERENCE ZO • W. 375.0 IN. 


M.A.C. CU » 39.550 


FT. 




9COY LENGTH LB ■ 1290.3 


IN. 






ENGINEER^ 



FIGURE 

ELEVEN L! 



4.1.2.1- 

FT COEF? 



•31 
ICIENT 



INCREMENT 



55 











AL°HA 


(C€G> 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


rOX CCEG) 


r 


G 


H 


I 


J 


K 


L 


M 








ELEVON LIFT 


INCREMENT 








-40.000 


-0.03000 


-0.03400 


-0.04400 


-0 . 05300 


-0 . 06500 


-0.07700 


-0 . 08675 


-0 . 0950C 


-35.000 


-0. Oct- 00 


-0.03200 


-0.04100 


-0 . 05000 


-0.06100 


-0.07200 


-0.08075 


-0 . 0880 C 


-30.000 


-0.02600 


-0 . 03000 


-0.03800 


-0.04600 


-0 . 05600 


-0 . 06500 


-0.07450 


-0 . 082C0 


-25.000 


-0.02400 


-0.02900 


-0.03500 


-0. 04300 


-0.05200 


-0.06100 


-o.oesee 


-0.0750C 


-20.000 


-0.02200 


-0 . 02S00 


-0 . 03300 


-0 . 04000 


-0.04750 


-0.05500 


-0.06:75 


-C.C680C 


-15.000 


-0.01600 


-0.01900 


-0.02500 


-C . 03000 


-0.03600 


-0.04200 


-0.04537 


-0.051CC 


-10.000 


-0.01100 


-0.01300 


-0.01600 


-0.02000 


-0.02400 


-0.02900 


-0.03:25 


-0.034CC 


-5.000 


-0.00500 


-0.0 0500 


-0.00800 


-0.01000 


-0.01200 


-0.01400 


-0.0!55c 


-CO 1700 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


CO 


5.000 


0.01100 


0.C1MO0 


0.01700 


. 02000 


. 02085 


. 02000 


0.0I""75 


c.oi4o: 


10.000 


0.02200 


0.02900 


0.03400 


. 04000 


0.04171 


0.0400C 


0.0355C 


0.028CC 


15.000 


0.03500 


O.CN800 


0.05300 


0.05900 


0.0614C 


. 05900 


0.05C3C 


0.0350C 


20.000 


0.05600 


0.C5700 


0.07300 


. 07900 


0.08188 


. 079C0 


0.06352 


. 038CC 



A.. 1.2.1-3* 



O - — r-- 



9» Rockwell International 

Sp«c«Olv«ion 



ll 



MACH NUMBER 



i i i r 



.0 



u 

_J 

a 

a 



TT 



DELE CDEGD 

-50 -25 ?.,.,? 

i i i i i i i i i i 1 1 ' ^n 

; I I I I I i I I I n 




-.4 



-.6 



II ■ ' ■ ' : 



-30 



•15 



-10 



Mill 1111 ' 11 

-5 5 

ALPHA CDE6D 



20 



I I i I i i I I . 
25 30 



COF I ORATION 



BASELINE 0R91TER VEHICLE 
CENTER OF GRAVITY X0 • f S 1076.7 IN. 
OR YO • BL 0.0 IN. 

MOfENT REFERENCE ZO • U. 375.0 IN. 



REFERENCE DIMENSIONS 
WING AF£A SU - 2590.00 SQ.FT. 
WING SPAN BW ■ 78.055 FT. 
M.A.C. CW ■ 39.550 FT. 

ROPY LENGTH LB - l2 90-?_ ' N - _ 




-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



-0.07000 
-0 . 05900 
-0.04900 
-0 . 03900 
-0.02900 
-0.02200 
-0.01400 
-0.00700 
0.0 

O.C3H0O 
O.C0900 
0.01000 
O.C! 100 



-0.05500 
-0.04800 
-0.04100 
-0.03300 
-0 . 02600 
-0.01900 
-0.0130C 
-0.00600 
0.0 

0.00400 
. 00900 
0.01000 
0.01100 



-0.0H200 
-0.03700 
-0.03200 
-0.02900 
-0 . 02300 
-0.01700 
-0.01100 

-o.cosoo 

0.0 

0.00^00 
0.00900 
. 1 000 
0.01000 



-0.03300 
-0.03000 
-0.02700 
-0.C2H00 
-0.02100 
-0.01500 
-0.01000 
-0.00500 
.0 

.00700 
.01300 
.02000 



0. 

0. 
0. 
0. 



. 02800 



-0.02500 
-0.02400 
-0.02200 
- -0.02000 
-O.OtBOO 
-0.01400 
-0.00900 
-0.00500 
0.0 

0.0C300 
0.01700 
. 03 1 00 
. 04500 



-0.03000 
-0.02800 
-0. 02600 
-0.02400 
-0.02200 
-0.01500 
-0.01 100 
-0.00500 
0.0 

0.01100 
0.02200 
0.03900 
0.O5S00 



-0 . 03400 
-0.03200 
-0 . 03000 
-0 . 02800 
-0.02600 
-0.01900 
-0.01300 
-0 . 00600 
0.0 

0.01400 
0.028C0 
0.04800 
0.C6700 



-0.04400 
-0.04100 
-0.03800 
-0.03500 
-0.03300 
-0 . 02500 
-0.01600 
-0.00800 
0.0 

0.01700 
0.03400 
. 05300 
. 07300 



ENGINEER B^EL 

PATE_iBSZag 



FIGURE 4.1.2.1-32 
R FVON LIFT COEFFICIENT. 



INCREMENT 



4.1.2.1-35 



^r 72-SH-CCCC 1M 



"i* 



Rockwell International 

Space Division 



MACH NUMBER 



20.0C0 



-50 



DELE 

-25 



CDEGD 
o 



25 



UJ 
_J 
O 
O 



-.6 



T II 



T 



nii! 




i i i 



i i i I i 



Mil 



I i I 



III! 



^g^-i^P^^" 



i i I i i i i I i 



i I i i : i 



.]_!_]_! 



I 1 I 



' I I I ' I 1 



10 15 20 25 30 35 

ALPHA CCEGD 



HO 



45 



50 



CObF IGLRATION 




SASELIf^ 0R81TER VEHICLE 


REFEREXE t IfENSIONS 




CENTER OF GRAVITY XO « F5 1076.7 IN. 


WINS ART* c .x » 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPa* EW » 78.056 


FT. 


MOENT REFERENCE ZO - U. 375 IN. 


M.A.C. CW - 39.550 


FT. 




BCOY LENGTH '.8 - 1290.3 


IN. 



ENGIf^ER &£& 
DATE 97JMY& 



FIGURE 
E'-EVON L 



4. 1.2. 1 

IFT CGEF 



-33 

FICIENT 



INCREMENT 



55 











ALPHA 


(DEa') 








15.000 


20.000 


25.000 


30.000 


35.000 


40 . 000 


45.000 


50.000 


DELE CDEG) 


F 


G 


H 


I 


J 


K 


L 


M 








ELEvON LIFT 


IN RECENT 








-40.000 


-0.03000 


-0.03400 


-0.04400 


-0.05300 


-C. 06500 


-0.07700 


-0 . 08675 


-0.09500 


-35.000 


-0 . 02800 


-0.03200 


-0.04100 


-0.05000 


-C.061C0 


-0.07200 


-0 . 08075 


-0.08800 


-30.000 


-0.02500 


-0.03000 


-0.03800 


-0.04600 


-C . 056C0 


-0.05600 


-0.07450 


-0.08200 


-25.000 


-0.02400 


-0.02900 


-0.03500 


-0.04300 


-' . 05200 


-0.0B100 


-0.06650 


-0.07500 


-20.000 


-0.02200 


-0.02600 


-0.03300 


-0.04000 


-1.04750 


-0.05500 


-0.06175 


-0.05800 


-15.000 


-0.01600 


-0.01900 


-0.02500 


-0.03000 


- ' . 03600 


-0.04200 


-0.04687 


-0.05100 


-10.000 


-0.01100 


-0.01300 


-0.01600 


-0 . 02000 


-: .02400 


-0.02800 


-0.03125 


-0.03400 


-5.000 


-0.00500 


-0.00600 


-0.00800 


-0.01000 


-r .01200 


-0.01400 


-0.01552 


-0.01700 


0.0 


0.0 


0.0 


0.0 


0.0 


i.O 


0.0 


0.0 


0.0 


5.000 


0.01100 


0.Q140O 


0.01700 


. 02000 


u . 02C86 


0.02000 


0.01775 


0.01400 


'10.000 


. 02200 


0.02800 


0.03400 


0.04000 


C. 04171 


0.04000 


0.C355C 


0.02800 


15.000 


. 03900 


. 04800 


0.05300 


0.05900 


0.061^0 


0.05900 


0.05000 


. 03500 


20.000 


C . 05600 


0.06700 


. 07300 


. 07900 


0.08103 


. 07900 


0.06368 


0.038C0 



4.1.2.1-36 



^L 



n r > 



OC IM 



'1* 



Rockwell Intemattons 

Spaca Division 



VBAR 



0.005 to o.ce 

T ill 



DELE CDEG: 

-50 -25 25 

I i i i i I i i i < i i i i i t 



LLl 




30 35 

ALPHA CDE63 



CO^IGURATION 



BASELINE ORBITER VEHICLE 

CENTER Cf GRAVITY XO - FS 1076.7 IN. 

OR YD - BL 0.0 IN. 

I-OCNT REFEJ3ENCE ZO « H- 375.0 IN. 



IN 

REFERENCE DIPENSIOS 




WING AREA SW - 2690.00 


SO. FT. 


WING SPAN BW • 78.056 


FT. 


H.A.C CW - 39.550 


FT. 


eCOY LTNGTH LB - 1290.3 


IN. 



m f tree,) 



-HO. 000 

-35.000 

-30.000 

-25.000 

-20.000 

-15.000 

-10.000 

-5.000 

0.0 

5.000 

10.000 

15.000 

20.000 



20.000 
A 



25.000 
B 



30.000 
C 



ALP HA (DEGl.. 
35.000 




^0. 000 

E 



45.000 

F 



50.000 
G 



ELEVON LIFT INCREMENT 



-0.03400 
-0.03200 
-0.03000 
-0.02800 
-0.02600 
-0.01900 
-0.01300 
-0.00600 
0.0 

0.01HOO 
0.02800 
0.04800 
0.06700 



-0.04400 
-0.04100 
-0.03B00 
-0.03500 
-0.03300 
-0.02500 
-0.01600 
-0.00800 
0.0 

0.01700 
0.03H00 
0.05300 
0.07300 



-0.05300 
-0.05000 
-O.0H6O0 
-0.04300 
-0.04000 
-0.03000 
-0.02000 

-o.oiaoo 
o.o 

0.02000 
0.04000 
0.05900 
0.07900 



-0.06500 
-0.06100 
-0.05600 
-0.05200 
-0.04750 
-0.03600 
-0.02400 
-0.01200 
0.0 

0.02086 
0.04I~1 
0.061 -0 
0.081S8 



-0.07700 
-0.07200 
-0.06600 
-0.06100 
-0.05500 
-0.04200 
-0.02S00 
-0.01HC0 
0.0 

0.02000 
. 04000 
0.05900 
0.07900 



-0.08675 
-0.08075 
-0.07450 
-0.06950 
-0.06175 
-0.04687 
-0.03125 
-0.01562 
0.0 

0.01775 
0.03550 
0.05000 
0.06362 



-0.09500 
-0.08800 
-0.08200 
-0.07500 
-0.06800 
-0.05100 
-0.03400 
-0.01700 
0.0 

0.01400 
0. 02300 
0.03500 
0.03800 



I ENGINEER 
DATE 



NASA 



FIGURE 4.1.2.1-34 

FFFECT CF ELEVON 



4.1.2.1-37 



s n 7 



D72- 



SH 



■CCCC 1M 



'1* 



Rockwell International 

SpacaONaion 



ft 

-I 

•3L 




0.5 



1.0 



1.3 2.0 a.5 

MACH NUMBER 



3.0 



3.5 



H.O 



— " CONFIOKATION 

Oien !KF «®ITER VEHICLE REFERENCE DIfCNSIOS 

CEKTCR^C^vm » ^076.7 IN. Wl* AREA W ; »0.00 9Q.n. 

OB Y0 " SL 0.0 IN. UINC SPAN 9W - TJ-CSS FT. 
^HT ^OCE ZC ■ H. *».0 IN. gfrC.^ « ■ 39.5^ FT. 



0.250 
0.H00 
0.600 
0.800 
0.900 
0.950 
0.980 
1.050 
1.100 
1.200 
1.300 
1.500 
2.000 
3.000 
4.000 
5.000 
8.000 
10.000 
15,000 
go -000 



-5.000 

_4 



rp g lCg ' 3 'i 



0.0 



LIFT PtBTIALSP^t 



5.000 



"0.60000 
0.60000 
0.60000 
0.69000 
0.80000 
0.S3000 
0.8M000 
0.8*000 
0.83000 
0.80000 
0.75000 
0.66000 
0.50000 
0.50000 
0.60000 
0.60000 
0.60000 
0.50000 
0.60000 



0.S0000 

0.60000 

0.60000 

O.S5000 

0.73000 

0.76000 

0.77000 

0.78000 

0.77500 

0.75000 

0.70000 

0.63000 

0.60000 

0.60000 

0.60000 

0.50000 

0.60000 

0.60000 

0.60000 



FACTOR 



0.60000 
0.60000 
0.60000 
0. 58000 
0.57000 
0.58000 
0.59000 
0.61000 
0.62000 
0.63000 
0.62000 
0.60000 
0.50000 
0.60000 
0.60000 
0.60000 
0.60000 
0.60000 
0.60000 
■ 0CQQ„ 



NOTE: In th« ev«nt »*rti«l 
span f»c:on »r» 
r«flui'r«c -Mien *xc««d 
tn«"jlven limits, tn« 
A«ro D«c» unic *c 
HocKw«! I lnt*rn«tlon'l 
ihould 3« eentactad 
b*f;r* ixtr»BOi»tion 
o^ tft« ;iv«n 4«c». 



ENGINEER &&P 
DATE. 






FIGURE 4.1.2.1-36 

Fl FVHN PARTIAL SPAN FACTOR 



4.1.2.1-39 



£ D 1L-GH-CCC0 1M 



#J* 



Rockwell International 

SpacwOiviMon 



MACH NUMBER 



0.250 



DELBF CDEG) 

-35 25 

f~n 1 | i i i i 



u. 

CD 
C 

o 




-.03 



-.OH 



5 10 

ALPHA CDEG} 



COflGLRATICN 



BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO - FS 1075.7 IN. 
OR YO « BL 0.0 IN. 

fOtMT REFERENCE 20 - UL 375.0 IN. 



REFERENT OlhCNSIONS 
WING AREA S-l - 2590.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW • 39.550 FT. 

BCOY LENG'- 1 -B - 1390.3 IN- 











ALMA 


tC£G> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF 10EG1 


A 


B 


C 


D 


E 


F 


G 


H 






B00Y 


FLAP LIFT F 


0RC£ INCREM 


ENT 






-11.700 


-0 . 03220 


-0.03220 


-0.03220 


-0.03220 


-0.03220 


-0.03220 


-0 . 03220 


-0.03220 


-5.000 


-0.01374 


-0.01377 


-0.01379 


-0.01379 


-0.01379 


-0.01379 


-0.01379 


-0.01379 


0-0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01370 


0.01377 


0.01380 


0.01380 


0.01380 


0.01380 


0.01380 


0.01380 


10.000 


0.0273* 


0.02755 


0.02761 


0.02761 


0.02751 


0.02761 


0.02761 


0.02761 


16.300 


0.34460 


0.04497 


0.04520 


0.04520 


0.04520 


0.04520 


0.04520 


0.04520 


£2.500 


0.07900 


0.07860 


0.077BO 


0.07669 


0.07500 


0.07145 


. 06790 


0.06790 



ENGINEER !**«*- 
Oate JLrJGtE?* 



FIGURE 4.1.2.1-37 

EFFECT OF BODY FLAP 



4.1.2.1-40 



SL TC-SI-.-CClC IM 



'1* 



Rockwell International 

Spae»Oi v on 



03 



T 



MACH NUMBER 
•'°; I I i i | I I i i| I I i 



0.400 
1 I I I 



5 .n? 



I I i 1 




0ELBF CDEG) _ 

-25 <» 

[ I I I I | I I i i 1 

r~r-r 



rm 



tt 



-.04 



5 10 

ALPHA CDEG3 



CONFIGURATION 



BASELINE CR8ITER VEHICLE 

CENTER CF GRAVITY XO » FS 1076.7 IN. 

OR YO - SL 0.0 IN. 

MOrENT REFERENCE ZO ■ U. 375.0 IN. 



REFERENCE DIfCNSIONS 
WING AREA SW - 2690.00 SQ.FT. 
MING SPAN BU - 78.056 FT. 
M.A.C. OJ - 39.560 FT. 

BODY LENGTH LB ■ 1590-3 IN. 



DELBF (PEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
52.500 



ALPHA 1CEG) 



-10.000 

A 



-5.000 
B 



0.0 

c 



5.000 
O 



10.000 

E 



15.000 

F 



50 . 000 
G 



25.000 

H 



BODY FLAP LIFT FORCE INCREhENT 



-0.03220 
-0.01374 
0.0 

0.01370 
0.02734 
0.04450 
0.07900 



-0.03220 
-0.01377 
0.0 

0-01377 
0.02755 
0.04497 
0.07860 



-0.03220 
-0.01379 
0.0 

0.01360 
0.02761 
0.04520 
0.07760 



-0.03220 
-0.01379 
0.0 

0.01380 
0.02761 
0.04520 
0.07669 



-0.03220 
-0.01379 
0.0 

0.01380 
0.02751 
0.04520 
0.07500 



-0.03220 
-0.01379 
0.0 

0.01380 
0.02761 
0.04520 
0.07145 



-0.03220 
-0.01379 
0.0 

0.01380 
0.02751 
0.04520 
0.06790 



-0.03220 
-0.01379 
0.0 

0.01380 
0.02761 
0.04520 
0.06790 



ENGINEER WH-1 2- 
HATE "4" Xg-7 8 



FIGURE 4.1.2.1-38 

FFFFCT OF BODY FLAP 



4.1.2.1- 



SD72-S! 



- cc c c 



IM 



€> 



Rockwell International 

SpacaOiviHon 



r 



MACH NUMBER 
'°r t | | | I i | | | 



CD 
_J 
U 
Q 



.08 



.06 



.04 



.02 



.0 



-.02 



.04 



0.600 

IIIF! 



DELBF CDEG3 

-25 25 



I I 1 I 



I I I I 



■15 




III! 



I I i I 



I I I I 



I I 1 I 



I I I I 



5 10 

ALPHA CDEG) 



15 



30 



30 



CONFIGURATION 


fcUStLINE ORBITER VEHICLE 


FErETOvCE DICEN5I0N5 


CENTER OF GRAVITY XO - FS 107E.7 IN. 


WING AREA SU - 2690.00 SQ.FT. 


OR YO - SL 0.0 IN. 


WING SPAN a- » 78.056 FT. 


MQ-ENT REFERENCE ZO - W_ 375.0 IN. 


M.A.C. CW • 39.560 FT. 




BODY LENGTH LB • 1230.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


11.000 


15.000 


20 . 000 


25.000 


DEL9F (OEG) 


A 


8 


C 





E 


F 


G 


H 






BCOY 


FLAP LIFT F 


ORCE INCREf-ENT 






-11.700 


-0.01990 


-0.01994 


-0.02267 


-0.02400 


-0.02476 


-0.02635 


-0.02635 


-0.02675 


-5.000 


-0.010t3 


-0.01042 


-0.01112 


-0.01150 


-0.01172 


-0.01218 


-0.0I21G 


-0.01218 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01574 


0.01520 


0.01455 


0.01358 


0.01433 


0.01393 


0.01393 


0.01393 


10.000 


0.03260 


0.03202 


0.03053 


0.02902 


0.02992 


0.02913 


0.02913 


0.02913 


15.300 


0.05400 


0.05359 


0.051! I 


0.05044 


0.35003 


0.04917 


0.04917 


0.04917 


22.500 


0.07530 


0.07525 


0.07162 


0.07345 


0.07028 


0.06970 


0.06970 


0.06970 



ENGINEER 
DATE 






FIGURE 4. 1.2. 1-39 

EFFECT OF BODY FLAP 



.1.2.1-U2 



SD 



■C "C 



r 



M 



e 



Rockwell International 

Space OtvMon 



MACH NUMBER 



0.800 



DELBF (DEC) 

-25 o 25 

| ! I i I | li't 



'0; | | | | I | | 1 I ' I I I I I I I I I 



.06 



Ll 
CD 

_J 



.02 



I 1 I I I I l 1 I I I I I I M I ' I ' ' ' 




CONF IGURATICN 



BASELINE ORSITER VEHICLE 



CENTER Of GRAVITY 

OR 
MOMENT REFERENCE 



XO - FS 1076.7 IN. 
YO - BL 0.0 IN. 
ZO ■ U. 375.0 IN. 



REFERENCE DlfENSIONS 
WIND AF£A SW » 2690.00 SQ.FT. 
WIND SPAN BW - 78.055 FT. 
M.A.C. CW - 39.550 FT. 

BCOY LENGTH LB - 1390.3 IN. 



-10.000 

A 



DELSF IQEG) 



-11.700 
-5.000 
0.0 
5.000 
10.000 
16.300 
22. SCO 



-5.000 
B 



0.0 

c 




WTVf n.AP LIFT FORCE INCRE'-ENT 



-0.02498 
-0.01202 
0.0 

0.01525 
0.03183 
0.0S312 
. 07449 



-0.02498 
-0.01202 
0.0 

0.01525 
0.03183 
0.05312 
. 07^49 



-0.02630 
-0.01238 
0.0 

0.01515 
0.03139 
0.05215 
0.07291 



-0.028H0 
-0.01306 
0.0 

0.01473 
0.03081 
0.05215 
0.07m IB 



-0.02855 


-0.02650 


-0.02900 


-0.02900 


-0.01327 


-0.01275 


-0.01381 


-0.01361 


0.0 


0.0 


0.0 


0.0 


0.01526 


0.01596 


0.01639 


0.01639 


0.03203 


0.03355 


0.03413 


0.03413 


0.05426 


0.05634 


0.05700 


0.05700 


0.07717 


0.07939 


0.08000 


. 08000 



EN3INEER_W<hZ. 
DATE ajiULl 7 1 



FIGURE 4.1.2.1-40 

FFFFr.T OF BODY FLA? 



4.1.2.1-43 



- <~ c; v.: 



CCCC 1M 



'1* 



Rockwell International 

Spac* Division 



MACH NUMBER 



0.900 



DELBF CDEGD 

-25 25 



m 

_l 



.10 



.08 



.06 



.04 



02 



.0 



-.02 



-.OH 



I I I I I I I I I I I I I l I l l 



I 1 L 



■■ I I 



I I 



I I I I 



I I I 




_L_L 



■■I..J.J-L 



I 1 I 



Tl I I | i i 



lit! 



_L_L 



I i I ! 



-15 



-10 



5 

ALPHA 



:0 
CDEGD 



15 



20 



30 



CONFIGURATION 


BASELINE 0RB1TER VEHICLE 


REFERENCE DIrENSIONS 


CENTER OF GRAVITY XO - FS 107S.7 IN. 


UIN3 AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 8W - 78.056 FT. 


K»ENT REFERENCE ZO • W- 375.0 IN. 


M.A.C. CW - 39.560 FT. 




9COY LENGTH L9 - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0EL9F <DEG> 


A 


8 


C 


D 


E 


F 


G 


H 






BODY 


FLAP LIFT F 


ORCE INCREM 


ENT 






-11.700 


-0.01955 


-0.01955 


-0.01973 


-0.01775 


-0.01950 


-0.01971 


-0.02000 


-0.02200 


-5.000 


-0.01105 


-0.01065 


-0.01009 


-0.00932 


-0.01027 


-0.01085 


-0.01105 


-0.01170 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01845 


0.01727 


0.01478 


0.01462 


0.01413 


0.01667 


0.01851 


0.01852 


10.000 


0.03985 


0.03623 


0.03100 


0.02952 


.0.03077 


0.03577 


0.03774 


0.03774 


16.300 


0.06400 


0.05857 


0.05010 


0.04830 


0.05313 


0.06057 


0.06200 


0.06200 


22.500 


0.08400 


0.07883 


0.06731 


0.06683 


0.07644 


0.08575 


0.08600 


. 06600 



ENGINEER Jj^iJ, 

date Z£iis:l>t 



FIGURE 4.1.2.1-41 

EFFECT OF BODY FLAP 



4.1.2.1- 



sr: 7 2-s;--:. orco m 



'1* 



Rockwell International 

SpacaDtviaion 



1_ 



I 



MACH NUMBER 



0.950 



DELBF CDEG3 

-25 25 



u. 
00 

_J 




■15 



-10 



5 10 

ALPHA CDEG) 



30 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO - B. 0.0 IN. 

MOtNT REFERENCE ZO « W- 375.0 IN. 



REFERENCE DIl^SIONS 

WING AREA SW - 2590.00 SQ.FT. 

WINS SPAN BW - 78.056 FT. 

M.A.C. CW " 39.560 FT. 

BODY LENGTH LB - 1290-3 IN. 



ALPHA CDEG) 



DELBF (CEO) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



-10.000 
A 



-5.000 
B 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



20.000 
G 



25.00C 
H 



-0.02500 
-0.0119+ 
0.0 

0.01489 
0.031 12 
0.05200 
0.07300 



9COY FLAP LIFT FORCE INCRPfKT 



-0.02430 
-0.01171 
0.0 

0.01515 
0.03134 
0.05195 
0.07249 



-0.02072 
-0.01036 
0.0 

0. 01*20 
0.02963 
0. 0493*t 
0.06905 



-0.01711 
-0.00841 

0.0 

0.01137 

0.0234m 
0.03S76 
0.C5399 



-0.01704 
-0.00829 
0.0 

0.01035 
0.02203 
0.03745 
0.05329 



-0.019S3 
-0.00938 
0.0 

0.C1O51 
0.02222 
0.03949 
0.05375 



-0.02400 
-0.01074 
0.0 

0.01123 
0.02294 
0.04000 
0.06200 



-0.02500 
-0.01106 
0.0 

0.01141 
0.02310 
0.04000 
0.CS400 



ENGINEER W*«K_ 
DATE AtiAt28 



FIGURE 4.1.2.1-42 

FFFFCT Cf BODY FLAP 



4.1.2.1-45 



sr 72-SH-ccec • \i 



'1* 



Rockwell International 

Sp*c*DMmot 



MACH NUMBER 

''° r I i I l l l i i l 



0.980 



DELBF CDEG: 

-25 25 



Ll 

m 



.08 



.06 



.04 



.02 



-.02 



.OH 



E 



L i. _!_. ' 



i I I I I i I 



I I I I 



Mil 



l l I I 



III! 1 I i I 




I I ! I I I I I 



I | i 



■J...L.L 



_!_!_ 



'—■ ^ J 



I I L 



-15 



•10 



5 10 

ALPHA CDEGD 



15 



a* 



30 



CONFIGURATION 




BASELINE ARBITER VEHICLE 


REFERENT Dlr-CNSICNS 




CENTER OF GRAVITY XO - FS 107B.7 IN. 


WING AREA 34 - 2690.00 


SQ.FT. 


OR YO " BL 0.0 IN. 


WING SPAN BU - 78.056 


FT. 


MCfCNT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW ■ 39.560 


FT. 




BCOY LENGTH LB « 1290. 3 


IN. 











ALPHA 


(KG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (KG) 


A 


8 


C 





E 


F 


G 


H 






BCOY 


FLAP LIFT F 


0RCE INCREM 


■NT 






-11.700 


-0.02346 


-0.02301 


-0.01998 


-0.01700 


-0.01696 


-0.02000 


-0.02450 


-0.02533 


-5.000 


-0.01098 


-0.01100 


-0.00994 


-0.00818 


-0.00809 


-0.00899 


-0.01045 


-0.01068 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.01242 


0.01341 


0.01316 


0.01006 


0.01029 


0.00955 


0.01039 


0.01035 


10.000 


0.02627 


0.02832 


0.02787 


0.02131 


0.02183 


0.01970 


0.02072 


0.02028 


16.300 


0.OH552 


0.04789 


0.04693 


0.03614 


0.03513 


0.03391 


0.03381 


0.03329 


22.500 


06669 


. 06787 


0.06635 


0.05t34 


. 04607 


0.0499O 


0.05205 


0.05413 



ENGINEER wmi. 
DATE I3K?*I-j'* 



FIGURE 4.1.2.1-43 

EFFECT 5F BODY FLAP 



4.1.2.1-46 



SE 



■ C c i 



C C C C 1 M 



#1% 



Rockwell International 

SpaccDMrton 



MACH NUMBER = 1-050 

• 10. | ) | | i | | | , I | I I I I I II 



CO 
_l 
o 
o 



DELBF CDEG) 

-25 » 

[ I I I I I I I I I I 

I I I I M I I I M I I I I ' I I I I i i i. 




-.02 



5 10 

ALPHA COEG) 



CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

OR YO - BL 0.0 IN. 

MO-ENT REFERENCE ZO - W. 375.0 IN. 



L 



REFERENCE Dlf^NSIONS 
WING AREA SU - 2690.00 SQ.FT. 
WING SPAN BW » 78.056 FT. 
M.A.C. CM - 39.550 FT.' 

BODY LENGTH LB ■ 1290.3 IN. 



DELBFJCEG) 



-11.700 
-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



ALPHA (DEG1 



-10.000 
A 



-5.000 
B 



0.0 

C 



5.000 
O 



10.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



BODY FLAP LIFT FORCE INCRErENT 



-0.01273 
-0.00657 
0.0 

0.00806 
0.01770 
0.03316 
0.05257 



-0.01*07 
-0.00737 
0.0 

0.01021 
0.02215 
0.03807 
0.05*55 



-0.01613 
-0.00802 
0.0 

0.0105* 
0.02235 
0.03776 
. 053*0 



-0.01747 
-0.0C81B 
0.0 

0.00937 
0.0)981 
0.03*09 
Q.CH92S 



-0.020*3 
-0.00915 
0.0 

0.0101* 
0.02129 
0.03*19 
0.0*1** 



-0.02008 
-0.00867 
0.0 

0.0C8S9 
0.01801 
0.02923 
0.038*9 



-0.02216 
-0.00929 
0.0 

0.00883 
0.01750 
0.02839 
. 03905 



-0.0227* 
-0.009*0 
0.0 

0.00861 
0.01659 
0.02732 
0.03S67 



ENGINEER ^^Jiz. 
DATE Zl->J>Z?l 



FIGURE 4.1.2.1-U. 

fFFfC.T OF BODY FLAP 



4.1.^.1-^7 



SD72-SH-CCCC 1M 



€* 



Rockwell International 

SpacaOivaion 



I 



MACH NUMBER 
■ io ( i i i i i | | — i — r 



1.100 



DEL6F CDEG) 

-25 25 



m 

_j 

CJ 
Q 




10 

CDEGD 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERECE DIf"EN5ICfS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


WING ARE/. SW - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU - 78.05S 


FT. 


MCfENT REFERENCE ZO - WL 375 IN. 


M.A.C. CW - 39.560 


FT. 




BOOY LEMTH LB - I2S0.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CEL9F (CEG! 


A 


B 


C 





E 


F 


G 


H 






80OY 


FLAP LIFT F 


ORCE INCPEM 


ENT 






-11.700 


-0.00800 


-0.01010 


-0.01427 


-0.01742 


-0.02100 


-0.01951 


-0.01950 


-0.01950 


-5.000 


-0.00466 


-0.00558 


-0.00705 


-0.00811 


-0.00931 


-0.00833 


-0.00825 


-0.00817 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00637 


0.C0780 


0.00894 


0.00918 


0.01009 


0.00833 


0.00817 


0.00791 


10.000 


0.01455 


0.01746 


0.01918 


0.01S35 


0.02101 


0.01666 


0.01627 


0.01559 


16.300 


0.02800 


0.03131 


0.03286 


0.03330 


0.03382 


0.02711 


0.02600 


0.02500 


22.500 


0.04500 


0.04654 


0.04705 


0.04817 


0.04146 


0.03409 


0.03400 


O.C3400 



ENGINEER UJ*1. 
DATE j5rj£»~5ft 



FIGURE 4.1.2.1-^5 
EFFECT OF BCOY FLAP 



4.1.2.1-48 



SD72-GH-G 



C ; - <*, I .Y 



* 



Rockwell International 

SpK* DiviMOn 



1- 



MACH NUMBER 
•i°1 l t I I 



1.200 



DELBF CDEGD 

-25 25 

| I I I I | i i i i | 



.06 



u. 

CD 

_J 




5 10 

ALPHA CDEGD 



30 



CONFIGURATION 



BASELINE ORBITER VEHICLE 

CENTER OF GRAVITY XO » FS 1075.7 IN. 

OR YO » BL 0.0 IN. 

MCr-ENT REFERENCE ZO - H- 375.0 IN. 



REFERENCE OI^ENSIONS 




MING AREA SW - 2690.00 


SQ.FT. 


WIND SPAN BW - 78.056 


FT. 


M.A.C. CW - 33.560 


FT. 


RfTOY LENGTH LB « 1290.3 


IN. 



ALPHA (PEG) 



CELBF (0EO1 



-11.700 

-5.000 

0.0 

5.000 
10.000 
16.300 
22.500 



-10.000 
A 



-5.000 
B 



0.0 

c 



5.000 
D 



10.000 

E 



15.000 
F 



20.000 

G 



25.000 
H 



BCOY Fl AP LIFT FORCE INCREMENT 



-0.00800 
-0.00480 
0.0 

0.00791 
0.01741 
0.03000 
. 04300 



-0.0097B 
-0.00545 
0.0 

0.00886 
0.01859 
0.03099 
0. OH 339 



-0.01352 
-0.00659 
0.0 

0.00775 
0.01669 
0.02986 
. QH500 



-0.01510 
-0.00736 
0.0 

0.00937 
0.01982 
0.03343 

0.04726 



-0.01138 
-0.00622 
0.0 

0.00929 
0.02011 
0.03432 
0.04887 



-0.01249 
-0.00598 
0.0 

0.00750 
0.01629 
0.02511 
0.03347 



-0.01200 
-0.00574 
0.0 

0.00734 
0.01552 
0.02500 
0.03300 



-0.01000 
-0.00509 
0.0 

0.00729 
0.01553 
0.C2500 
O.C33C0 



ENGINEER w£*Z. 

DATE ArJiZzlS 



FIGURE 4.1.2.1-46 

FFFFCT OF BODY FLAP 



4.1.^.1-49 



SD72-Sn-CCeC'lM 



#1% 



Rockwell International 



MACH number 



1.300 



DELBF CDEGj 

-55 25 

i i : 



CD 

_l 



.10 



.08 



.06 



.04 



.02 



-.02 



.04 



_L_L 



m i I i i m i iii i i i i i i i i i i 




i i i i 



i ) l 



S2± 



* 




'iii 



i i i i 



i i.. i 



i I i I 



i.i ,1 i„ 



-15 



-10 



5 
ALPHA 



10 

CDEG) 



15 



2Q> 



25 



30 



CO>FIGLRATICN 


BASELINE ORBITER VEHICLE 


REFERENCE DirENSIGNS 


CENTER CF GRAVITY XO • FS 1078.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 FT. 


MCtCNT REFERENCE 20 • WL 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BCOY LENGTH LB » 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.00C 


0.0 


5.000 


0.000 


15.000 


20.000 


25.000 


DELBF (OEO) 


A 


8 


C 





E 


F 


G 


H 






BCOY 


FLAP LIFT F 


CfiCE INCREM 


ENT 






-11.700 


-0.00500 


-0.00580 


-0.00941 


-0.01103 


-0.01195 


-0.01254 


-0.01200 


-0.01200 


-5.000 


-0.00346 


-0.00412 


-0.00505 


-0.00589 


-0.00636 


-0.00640 


-0.00581 


-0.00574 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00713 


0.00770 


0.00828 


0.00902 


0.00958 


0.00894 


0.00771 


0.00722 


10.000 


0. 01500 


0.01607 


0.01663 


0.01960 


0.02113 


0.01998 


0.01608 


0.01502 


16.300 


0.02500 


0.02501 


0.02718 


0.03140 


0.03369 


0.03163 


0.02500 


0.02500 


22.500 


0.03500 


0.03518 


0.03740 


a . 04064 


0.04236 


0.03679 


0.03500 


. 03500 



ENGINEER £**— 

date lArkr5% 



FIGURE 4. 1.2. 1-47 

EFFECT OF BODY FLAP 



4.1.2.1-50 



SD 72-SH-CCCC ifvl 



'1* 



Rockwell International 

Spac* Division 



1_ 



MACH NUMBER = 1.500 

■ 10 . | | M | | i i i | ll M I I I l i I M i i i i I 



OELBF CDEGD 

-25 25 

| i I I i | i i- t i 1 

I I I I I i 



CD 

_J 
U 

a 




-.04 



-15 



ALPHA COEG) 



CONFIGURATION 



BASELINE ORBI'ER VEHICLE 

CENTER OF GRAVITY XO - FS 1076.7 IN. 

OR YO ■ SL 0.0 W. 

HDftfJT REFERENCE 20 « U. 375.0 IN. 



REFERENCE DIMENSIONS 
W1N3 AREA SVI • 2690.00 SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CW • 39.560 FT. 

BODY LENGTH LB - 1390.3 IN. 











ALPHA 


(DEC) 


■ 






-10.000 


-5.000 


0.0 


5.0DO 


10.000 


15.000 


20.000 


25.000 


OELBF (OEG) 


A 


e 


C 


D 


E 


F 


G 


H 






BODY 


FLAP LIFT F 


ORCE INCREM 


EMT 






-11.700 


-0.00372 


-0.01057 


-0.01019 


-0.00965 


-0.01059 


-0.01354 


-0.01470 


-0.01468 


-5.000 


-0.00451 


-0.00487 


-0 . 00484 


-0.00498 


-0.00541 


-0.00S23 


-0.00654 


-0.00657 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00544 


0.00574 


. D0604 


0.00709 


0.00756 


0.00730 


0.00716 


0.00728 


10.000 


0.01IHI 


0.01211 


0.01297 


0.01537 


0.01702 


0.01554 


0.01494 


0.01523 


16.300 


0.01840 


0.01949 


0.02077 


0.02513 


0.02687 


0.02489 


0.024C5 


0.02451 


1 22.500 


0.02438 


0.02532 


0.02633 


0.029-4 


0.03006 


0.03088 


0.03006 


. 0309 1 * 



ENGINEER ^Cit 

OATE iiiZizls 



FIGURE 4.1.2.1-45 

FFFFCT OF BODY FLAP 



U. 1.2 .1-51 



SD 72-3H-CCCC 1M 




Rockwell International 

Space DMtfori 



MACH NUMBER 
• l0 | I I I I I I i i'T' 



2.000 



Li. 
QD 

_J 
O 

a 



.OB 



.06 



.OH 



.02 



-*=w- 



-.02 — 



-.OH 



lit! 



TT 



i i i I i i i i 



II I I I I I I 




I I I ! I I 



DELBF CDEGD 

- 25 . 25 

I' I l I'l | I I ■ I | 

I l I I 



I I I I I I I I I I I I I 1 I 



I I I I I I I 1 



I I I ! I 1 



-15 



5 10 15 

ALPHA CDEGD 



SO 



30 



35 



CONFIGURA' 


ION 




BASELY CRSITER VEHICLE 


REFERENCE OlrCNSIONS 




CLNTER OT GRAVITY X0 • FS 107S.7 IN. 


WING AREA St- - 2690.00 


sa.rr. 


OR YO • BL 0.0 IN. 


WING SPAN BH - 78.056 


FT. 


MOfCNT REFERENCE ZO • U. 375.0 IN. 


M.A.C CW » 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 





ALPHA (CEG) 






-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


30 . 000 


OELBF (CEG) 


A 


B 


c 





E 


F 


G 


H 


I 








BCOY FLAP LIFT FORCE 


INCREMENT 








-11.700 


-0.00200 


-0.00300 


-0.00439 


-0.00715 


-0.00944 


-0.01142 


-0.01246 


-0.01300 


-0.01319 


-5.000 


-0.00160 


-0.00200 


-0.002H9 


-0.00348 


-0.00429 


-0.00503 


-0.00552 


-0.00577 


-0.0C59C 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00370 


0.00396 


0.00429 


0.00455 


0.00498 


0.00540 


. 00597 


0.00630 


0.00525 


10.000 


0.0081! 


0.00876 


0.00891 


0.00978 


0.01025 


0.01115 


0.01241 


0.01298 


0.01287 


16.300 


0.01300 


0.01H00 


0.01444 


0.01568 


0.01662 


0.01800 


0.02000 


0.02100 


0.C22OO 


22.500 


0.01700 


0.01800 


0.01958 


0.02015 


0.02250 


0.02291 


0.02500 


. 02900 


0.03500 



ENGINEER w *l 

oate 3.z±.°:13 



FIGURE 4.1.2.1-49 

EFFECT OF BODY FLAP 



4.1.2.1-5? 



SD72 



3H 



ccec im 



*i* 



Rockwell International 

SpacaDtvmnn 



MACH NUMBER 
■>°l i I l I I I i 



3.000 



DELBF CDEG] 

25 25 



u. 

CD 
_J 
CJ 
Q 




5 10 

ALPHA CDEG) 



CONFIGURATION 



BASELINE ORBITER VEHICLE 
CENTER Cf" GRAVITY XO « FS 1075.7 IN. 
OR YO - a. 0.0 IN. 

fO"ENT REFERENCE ZO ■ WL 375.0 IN. 



REFERENCE OlrENSICNS 
WING AREA SW - 2S90.CO SQ.FT. 
WING SPAN BW - 78.056 FT. 
M.A.C. CM - 39.560 FT. 

BCOY I FNRTH LB ■ 1290.3 IN. 





_ , 


. 


— . — 


ALPHA 


(DEG) 








-10.000 


-5.000 


0.0' 


5.000 


10.000 


15.000 


20.000 


25.000 


OELSF (DEG) 


A 


B 


c 


D 


E 


F 


G 


H 






BCOY 


FLAP LIFT F 


OflCE INCREM 


:nt 




■■ 


-11.700 


-0.00050 


-0.00180 


-0.00222 


-0.00372 


-0.00478 


-0.00500 


-0.00756 


-0 . 00957 


-5.000 


-0.00046 


-0.00099 


-0.00124 


-0.00IB7 


-0.00238 


-0.00297 


-0.00361 


-0.00435 





0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00032 


0.00137 


0.00169 


0.00258 


0.00321 


0.00403 


0.00477 


0.00495 


10.000 


0.00201 


0.00306 


0.003S1 


0.00541 


0.00674 


0.00869 


0.00960 


0.01024 


16.300 


0.00400 


0.00550 


0.00707 


0.00902 


0.01126 


0.01393 


0.01564 


0.01707 


22.500 


0.00650 


. 00620 


0.01089 


0.012SH 


0.01584 


0.01800 


0.02153 


. u2Jib 



ENGINEER W«"»- 

oate ZizJJizl * 



FIGURE 4.1.2.1-50 

EFFECT OF BODY FLAP 



..1.2.1-53 



SC72-SK-CCeC IM 



* 



Rockwell International 

Spw* Olvwion 



NUMBER 



DELBF CDEG) 

o 25 

i i i 



H 




25 30 35 

ALPHA CDEG 3 



CONFIGURATION 




BASELINE 0RB1TER VEHICLE 


REFERENCE OIrt>6ICNS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


MING AREA SU « 2690.00 


SQ.FT. 


OR vo -. a. 0.0 IN. 


WIM3 SPAN BU - 78.055 


FT. 


MCfCNT REFERENCE ZO - UL 375.0 IN. 


H.A.C. Ol « 33.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 





ALPHA (CEG) 


15.000 


20 . 000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELBF (CEG) 


F 


G 


H 


I 


J 


K 


L 






BCOY FLAP LIFT FORCE 


INCREMENT 






-11.700 


-0.00600 


-0 . 00756 


-0.00957 


-0.01050 


-0.01200 


-0.01350 


-0.01500 


-5. COO 


-0.00297 


-0.00361 


-0.00436 


-0.0048! 


-0.00544 


-0.00604 


-0.00660 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00H03 


0. 004 77 


0. 00495 


0.00539 


. 00608 


0.00659 


0.00692 


10.000 


0.00369 


0.00960 


0.01024 


01124 


0.01258 


0.01354 


0.01413 


16.300 


0.01393 


0.01554 


0.01707 


0.01900 


0.02100 


0.02250 


0.02350 


22.500 


■ 0.01800 


0.02153 


0.02395 


0.02700 


0.02950 


0.C3150 


0.03300 



ENGINEER '-U**z 

oate Z3Z-5e-35 



FIGURE 4.1.2.1-51 

EFFECT OF BODY Ft 



AP 



4.1.2.1-5^ 



S D 1 £ - 



CCCC 1M 



€* 



Rockwell International 

Spaca Division 



L_ 



MACH NUMBER 

•10| I I I I I f 1 I I | I I 



DELBF CDEG 

-25 25 



n 



CD 




5 10 

ALPHA CDEGD 



CONFIGURATION 



BASELIKE CR9ITER VEHICLE 

CENTER OF GRAVITY XD » FS 1076.7 IN. 

OR YO - BL 0.0 IN. 

MOt-ENT REFERENCE ZO • U. 375.0 IN. 



REFERENCE DIMENSIONS 

UING AREA SW - 2590.00 SQ.FT. 
WING SPAN BU - 78.056 FT. 
H.A.C. CW - 39.560 FT. 

BODY I FNGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BODY 


FLAP LIFT F 


ORCE INCREM 


£NT 






-11.700 


0.0 


-0.00085 


-0.00160 


-0.00220 


-0.00290 


-0.00440 


-o.oosoo 


-0.00755 


-5.000 


-0.00002 


-0.00038 


-0.00078 


-0.00125 


-0.00172 


-0.00250 


-0.00329 


-0.00414 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00007 


0.00039 


0.0009H 


0.00209 


0.00321 


0.00402 


0.00466 


0.00674 


10.000 


0.00020 


0.00080 


0.00201 


0.00451 


0.00682 


0.00863 


0.01034 


0.01390 


16.300 


0. 00030 


0.00136 


O.OQ350 


0.00725 


0.0! ICO 


0.01460 


0.01320 


0.02295 


1 22.500 


0.0 


0.00199 


0.00510 


0.C0952 


0.01470 


0.02065 


o.oeeeo 


0.03194 



ENGlNEER„mft3«.- 
DATE izl9^% 



FIGURE 4.1.2.1-52 

FFFFCT OF BODY FLAP 



..1.2.1- 5 



SD 72 -SH-CCCC 1M 



#1% 



Rockwell International 

Space Division 



MACH NUMBER 



CD 

_J 
U 

o 



.10 



.08 



.06 



.OH 



.02 



-.02 



"f^H 



T' I I I 



4.000 
i i i i I r 



DELBF CDEG) 

-25 25 



0t . i i i i I l l l l 

io J5 ao 



T~r 




i i i i i i i 



i i r 



I I I I 



1 ' ■ ' t 
I I i i 



! I I 



I I 1 I I I 1 I i 



I 1 I I 



J 



25 30 35 

ALPHA CDEG3 



W , 



45 



50 



OFIGLRA1 
BASELINE ORBITER VEHICLE 
CENTER OF GRAVITY XO » FS 1076 7 IN. 
CR YO - BL 0.0 IN. 


riON 


REFERENCE DI^E^6IC^E 
WIM3 AREA SW - 2690.00 SQ.FT. 
WING SPAN Bw » 78.056 FT. 
M.A.C. Crl - 39.550 FT. 
BCCY LENGTH LS ■ 1290.3 !N. 


I-OTENT REFERENCE 20 • U. 375.0 IN. 





ALPHA (DEO) 






15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


CCLBF (DEO J 


F 


G 


H 


I 


J 


K 


L 






900Y FLAP LIFT FORCE 


INCREMENT 






-11.700 


-0.00440 


-0.00600 


-0.00755 


-0.00910 


-0.01120 


-0.01330 


-0.01517 


-5.000 


-0.00250 


-0.00329 


-0.00414 


-0.00499 


-0.00573 


-0.00536 


-0.00685 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00402 


0.00466 


0.00674 


0.00800 


0.00818 


0.00805 


0.00774 


10.000 


0.00863 


0.01034 


0.01390 


0.01724 


0.01782 


0.01739 


0.01632 


16.300 


0.01460 


0.01820 


0.02295 


0.02770 


0.02850 


0.C2780 


0.02620 


22.500 


0.02065 


0.02660 


0.03194 


0.03640 


0.03S37 


0.03480 


0.03242 



ENGINEER UH.V 
DATE 5rJJi:">t 



FIGURE 4.1.2.1-53 

EFFECT OF BODY FLAP 



4.1.2.1-5* 



bD'2 



C l.l 
-Oil 



■ U k_ 



O IM 



#1% 



Rockwell International 

SpecmOMmon 



i- 



MACH NUMBER = 5.000 

■ 10. | | | , I f 1 I I | t I I I | I I I 



DELBF CDEGD 

25 25 

I I I I | I l I I 








-.02 











CONF 


GURAT 


BASELINE 0R9ITER 


VEHICLE 




CENTER 


OF GRAVITY 


XD 


- FS 


1076.7 


IN. 




OR 


YO 


- a. 


0.0 


IN. 


MOMENT 


REFERENCE 


ZO 


• u. 


375.0 


IN. 



ENGINEER l*""jfc_ 
OATE HEACrUI 



REFERENCE Dir-ENSICNS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW • 78.056 FT. 
M.A.C. OJ - 39.560 FT. 

BOO- LENGTH LB - 1290.3 IN. 











4LPHA 


<CEG> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DF1.FF (DEG1 


A 


B 


c 


D 


E 


F 


e 


H 






BCOY 


FLAP LIFT FORCE INCREM 


ENT 






-11.700 


0.0 


-0.00069 


-0.00140 


-0.30213 


-0.0C290 


-0.00445 


-0.00600 


-0.00745 


-5.000 


0.0 


-0.00018 


-0.00051 


-0.00106 


-0.0C152 


-0.00242 


-0.00321 


-0.00404 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00012 


0.00028 


0.00143 


0.0026S 


0.00376 


0.00450 


0.00669 


10.000 


0.0 


-0.00OH2 


0.00039 


. 0.00309 


0.00572 


0.00791 


0.0C988. 


0.01355 


16.300 


0.0 


-0.00052 


0.00070 


. 00495 


0.00920 


0.01320 


0.01720 


0.02205 


22.500 


0.0 


-0.00046 


o.oo mo 


. 00632 


0.01210 


0.01850 


. 02490 


. 03027 



FIGURE 4. 1.2. 1 -51 

EFFECT OF BOPY FLAP 



t. 1.2. 1-57 



SD 72-SH-OCCC 1M 



'1* 



Rockwell International 



OELBF CDEG1 

25 25 



CD 
_1 
_) 

a 




Of I CURAT I ON 




BASELINE CRBITER VEHICLE 


►fcJ-U4.NO. UlftNblUNb 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SU - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOCENT REFERENCE 20-14. 375.0 IN. 


M.A.C. Cw - 39.560 


FT. 




BCOY LENGTH LS - 1290.3 


IN. 











ALPHA 


tOEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


PP. PF (HFC,) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP LIFT F 


ORCE INCREM 


£NT 






-11.700 


-0.00445 


-0.00600 


-0.00745 


-0.008SO 


-0.01105 


-0.01320 


-0.01535 


-0.01750 


-5.000 


-0.00242 


-0.00321 


-0.00^04 


-0.00487 


-0.00562 


-0.00627 


-0.00685 


-0.00736 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00376 


0.00450 


0.00669 


0.00767 


0.00792 


0.00781 


0.00754 


0.00726 


10.000 


0.00791 


0.00986 


0.01355 


0.01683 


0.01728 


0.01682 


0.01578 


0.01448 


16.300 


0.01320 


0.01720 


0.02205 


0.02690 


0.02762 


0.02690 


0.02536 


0.02280 


22.500 


0.01850 


0.02490 


0.03027 


0.034*0 


0.03503 


O.03T7O 


0.03095 


0.02550 



ENGINEER ^j»w t, 
D ATE Z„2.'.\A-t 



FIGURE 4.1.2.1-55 

EFFECT OF BODY -LAP 



4.1.2.1-58 



SD 72-SH-CCCC 1M 



'J* 



Rockwell International 

Spac*Oiv»on 



MACH NUMBER 



8.00C 



DELBF CDEG) 

-25 25 

I I I I I I I I I I 1 



' ! I ! ! 



CD 

_1 



.08 



.06 



.04 



.03 



.02 



■ A -A 



>. * , i t-aAC'A.S a S ' e 



J_L 



Till 



i ii ii . i i i — r 



'iii 



_L_L 



_L 




n rr~i r 



Y=*»c*:=**G= = &#r 



i ' i 



=s* 



-10 



5 10 

ALPHA CDEG) 



15 



20 



30 



T 



COKFIGLRATION 




BASELINE ORSITEB VEHICLE 


REFERENCE 0I^ENSI0NS 




CENTER CF GRAVITY XD - FS 1075.7 IN. 


UING AREA SW ■ 2S90.00 


SQ.FT. 


CR YO • BL 0.0 IN. 


WING SPAN BU » 78.056 


FT. 


MOENT REFERENCE 20 - W_ 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH L9 ■ 1290.3 


IN. 











ALPHA 


(□EG) 








-10.000 


-5.000 


0.0 


.000 


10.000 


15.000 


20 . 000 


25.000 


0ELSF (DEG) 


A 


8 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP LIFT F 


ORCE INCREM 


ENT 






-11.700 


-0.00030 


-0.00084 


-0.00140 


-0.00198 


-0.00260 


-0.00370 


-0.00500 


-0.00638 


-5.000 


-0.00010 


-0.00020 


-0.00046 


-0.00091 


-0.00142 


-0.00210 


-0.00285 


-0.00363 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00006 


-0.00028 


0.00015 


0.00105 


0.00216 


0.00345 


0.00484 


0.00615 


10.000 


0.00007 


-0.00061 


0.00012 


0.C0230 


0.00496 


0.00769 


0.01C38 


0.01313 


16.300 


0.0 


-0.00098 


0.0 


0.00366 


0.00780 


0.01225 


0.01670 


0.02115 


22.500 


-0 . 00020 


-0.00130 


-0 . 00020 


0.00343 


. 00960 


0.01535 


0.02210 


0.02809 



ENGINEER Wvwt_ 
DATE 'J^zY&C^ 



FIGURE 4.1.2.1-56 
EFFECT OF BCOY FLAP 



L. 1.2. 1-59 



£D7 2 -SH-CCCC 1M 



'1* 



Rockwell International 

Spj»c« Diviwon 



J_ w 



MACH NUMBER = 8.000 

10 [ I l ii 1 l I I I i I I I I ! I l I 



DELBF CDEG) 

-25 25 

I I ' i 



Li- 
CD 
_J 

u 
a 



.08 



.06 



.04 



.02 



-.02 



.OM 



I p-k ==&&!= =^ : z - 




l I 



J_i_L 



I I I 



I I i I I i 



^~^r~J- 



.I..1 L 1-1 I, 1 I I 




I .L.I.-L 



I I I I 



I I I I 



J_L 



10 



15 



20 



30 35 

ALPHA CDEG 3 



40 



45 



50 



CCNFIGLRA1 
. BASELINE GRBITER VEHICLE 


HON 


HfcJ-UfcNO. OlftNblONb 


CENTER OF GRAVITY X0 - FS 1076.7 IN. 


U NG AREA SW - 2690.00 SQ.FT. 


OR YO « BL 0.0 IN. 


U'.NG SPAN SU • 78.056 FT. 


M3-ENT REFERENCE ZO • W. 375.0 IN. 


M.A.C. CU - 39.550 FT. 




BCCY LENGTH LS • 1290.3 In. 











ALPHA 


!DEG) 








15.0C0 


20.000 


25.000 


30.000 


"^.000 


40.000 


45.000 


50.000 


DELBF <C€G> 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP LIFT F 


ORCE INCRErt 


lNT 






-11.700 


-0.00370 


-0.00500 


-0.00638 


-0.008CO 


-0.01055 


-0.01310 


-0.01539 


-0.01750 


-5.000 


-0.00210 


-0.00285 


-0.00363 


-0.00448 


-0.00539 


-0.00617 


-0.00678 


-0.00722 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00345 


0.00484 


0.00615 


0.0073! 


0.00763 


0.00757 


0.00725 


0.00699 


10.000 


0.00759 


0.01038 


0.01313 


0.01600 


0.01674 


0.01636 


0.01503 


0.01382 


16.300 


0.01225 


0.01670 


0.02115 


0.02560 


0.02570 


0.02610 


0.02421 


0.02090 


22.500 


0.01535 


0.02210 


0.02809 


0.03300 


0.03346 


0.03150 


0.027-9 


0.02210 



ENGIn£ER_J>OmT, 
DATE 5?AerT8 



FIGURE 4.1.2.1-57 
EFFECT GF BODY FLAP 



4. 1.2. l-6-i 



SC72-SH-CCCO IM 



'1* 



Rockwell International 

Spac«C*vtt^3n 



MACH NUMBER 
■ l0 i i l I I 



DEi-BF CDEG) 

-25 25 

| I I I I | i i I i 



u 

CD 

u 




5 10 

ALPHA CDEGD 



CONF 1GURATICN 



BASELINE ORB!TER VEHICLE 

CENTER CF GRAVITY XO » FS 1075.7 IN. 

CR YO - BL 0.0 IN. 

MOMENT F£FER£nC£ ZO - WL 375.0 IN. 



REFERENCE DIMEN5I0N5 
WIN3 AREA SU - 2630.00 SQ.FT. 
WING SPAN EW - 78.055 FT. 
M.A.C. CW » 39.560 FT. 

BCOY LFNSTH LB » 1290.3 IN, 





ALPHA (DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.00 


25.000 


DQ_9F (DEG) 


A 


8 


c 





E 


F 


G 


H 






ecoY 


FLAP LIFT FORCE INCREM 


£NT 






-11.700 


0.0 


-0.00067 


-0.00130 


-0.00185 


-0.00240 


-0.00342 


-0.00470 


-0.00613 


-5.000 


0.0 


-0.00015 


-0.00042 


-0 . 00086 


-0.00135 


-0.00203 


-0.00278 


-0.00354 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00023 


0.0 


0.00104 


0.00215 


0.00349 


0.00495 


0.00633 


10.000 


0.0 


-0.0006H 


0.0 


0.00227 


0.00498 


0.00783 


0.01062 


0.012S8 


16.300 


0.0 


'■ -o.ooose 


0.0 


0.00359 


0.00780 


0.01245 


0.01710 


0.02111 


22.500 


0.0 


-0.00104 


0.0 


0.00327 


0.00830 


0.0155O 


0.02370 


0.02894 



ENG[NEER_U*!i_ 

o ate _. ____9L-JVe/?3 



FIGURE 4.1.2.1-58 

EFFECT OF BODY FLAP 



4.1.2.1-61 



SC 72-SH-CC6C !M 



*J> 



Rockwell International 

Spac* DivMton 



MACH NUMBER 



a 



.10 



.08 



.06 



.04 



.02 



-.02 



.04 



"Till T"'l 



J_L 



10.000 



DELBF CDEG) 

-25 25 

111 



I I I -l 



I 1 



1 I ' I I 




1 I I 



i i r r 



i i i 



iT 



! 1 I 



; nT 

MM 



•-=ts±n 



10 



15 



20 



30 

ALPHA 



35 

CDEG 3 



to 



•« 



50 



55 



CONFIGURATION 


BASELINE ORBITER VEHICLE 


F&J-LHlNCE DIMENSIONS 


CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW - 2690.00 SQ.FT. 


CR YD ■ BL 0.0 IN. 


WING SPAN 9W - 78.055 FT. 


K>€NT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CM - 39.560 FT. 




BODY LENGTH LB • 1290.3 IN. 











ALPHA 


(DEC) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


OEL8F <0£G) 


F 


G 


H 


I 


J 


K 


L 


M 






BODY 


FLAP LIFT F 


ORCE INCREM 


E>fT 






-11.700 


-0.00342 


-0.00470 


-0.00613 


-0.00790 


-0.01075 


-0.01360 


-O. 01577 


-0.01750 


-5.000 


-0.00203 


-0.00278 


-0.00354 


-0.00436 


-0.00542 


-0.00637 


-0.00693 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00349 


0.00496 


0.00638 


0.00723 


0.00763 


0.00771 


0.00737 


0.00697 


10.000 


0.00783 


0.01062 


0.01298 


0.01481 


0.01631 


0.01659 


0.01525 


0.01376 


16.300 


0.01245 


0.01710 


0.02111 


0.02440 


0.02523 


0.02550 


0.02459 


0.02070 


22.500 


0.01550 


0.02270 


0.02994 


0.03390 


0.03446 


0.03230 


0.02794 


0.02120 



ENGINEER ujmt. 
DATE ZSYX^t 



FIGURE 4.1.2.1-59 
EFFECT OF BODY FLAP 



4.1.2.1-62 



ST72-SH-CCCC IM 



#1% 



Rockwell International 

Spac*Div«ton 



1- 



GO 



MACH NUMBER 



15.000 



DELBF CDEG) 

-25 25 



-.02 




5 10 

ALPHA CDEGD 



30 



CO.FIGLRATI0N 




BASELINE CRSITER VEt-'CLE 


REFERENCE DIMENSIONS 




CENTER OF GRAVITY XO ■ PS 107E 7 IN 


WING AREA 5U - 2690.00 


SQ.FT. 


OR YO • 8L 0.0 IN 


WING SPAN BW » 78.056 


FT. 


MCtt/.T REFfRENCE 20 - U. 375 IN 


M.A.C. CH - 39.550 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELBF (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






BCOY 


FLAP LIFT F 


ORCE INCREM 


ENT 






-11.700 


0.0 


-0.000S7 


-0.00130 


-0.00185 


-0.00240 


-0. 00342 


-0.00470 


-0.00613 


-5.000 


0.0 


-0.00015 


-0.00042 


-0.00086 


-0.00135 


-0.00203 


-0.00278 


-0.00354 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


o.: 


0.0 


5.000 


0.0 


-0.00023 


0.0 


0.00104 


0.00215 


0.00349 


0.00496 


0.00639 


10.000 


0.0 


-0.00C54 


0.0 


0.00227 


0.00498 


0.00783 


0.01062 


0.012S8 


15.300 


0.0 


-0.00098 


0.0 


0.00359 


0.00780 


0.01245 


0.01710 


0.02111 


22.500 


0.0 


-0.00! T4 


0.0 


. 0032~ 


. 00830 


0.01550 


0.02270 


C. 02894 



ENGINEER i*»i2. 
DATE "JGAJr** 



FIGURE 4.1.2.1-60 

EFFECT OF B3QY FLAP 



4.1.2.1-63 



SL72-SH-CCCC IM 



a 



Rockwell International 

Sp*c*Otauon 



_a_ 



MACH NUMBER 



15.000 



u. 
CO 



.10 



.08 



.05 



.04 



.02 



DELBF CDEGD 

25 25 

T"l I > I i I I I ! 



-.02 



.04 



T" 



_L_L 



I I I I 



I I I I 



■11 1 ! 



I I i I j I I I 



^ 




I I 



m ri i i i i 



-1_L 



s 



] I i 



I I I 



I 1 _L 



i i i r 



10 



15 



20 



25 



! I I I 



30 35 

ALPHA CDEG) 



HO 



45 



50 



55 



C0NF1ORA' 

BASELINE 0R8ITER VEHICLE 


now 


HLftHJJCL D1I-EN5ICNS 


CENTER CF GRAVITY XO • FS 1076.7 IN. 


WING AREA 3-1 - 2690.00 SQ.FT. 


OR YO • BL 0.0 IN. 


WING SPAN BU - 78.055 FT. 


K>£NT REFERENCE ZO - H_ 375.0 IN. 


M.A.C. CW - 39.550 FT. 




BODY LENGTH L8 - 1290.3 IN. 











ALPHA 


<0EG> 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45 . 000 


50.000 


OELSF lOEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP LIFT F 


0RCE INCREM 


ENT 




- 1 1 . 700 


-0.00342 


-0.00470 


-0.00613 


-0.00790 


-0.01075 


-0.01350 


-0.01577 


-0.01750 


-5.000 


-0.00203 


-0.00278 


-0.00354 


-0.00436 


-0.00542 


-0.00637 


-0.00693 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00349 


0.00496 


0.00638 


0.00723 


0.00763 


0.00771 


0.00737 


0.0C697 


10.000 


0.00783 


0.01062 


0.01298 


0.01481 


0.01631 


0.01659 


0.01526 


0.01376 


IS. 300 


0.01245 


0.01710 


0.02111 


0.02440 


0.02523 


0.02650 


0.02459 


. 02070 


22.500 


0.01550 


0.02270 


0.02894 


0.03390 


0.03446 


0.03230 


0.02794 


0.02120 



ENGINEER 
DATE ~ 



'.Kilt.--* 



FIGURE 4.1.2.1-61 
EFFECT OF BODY FLAP 



4.1.2.1-64 



SC72-SH-CCCC I 



M 



0^ 



Rockweil International 

SpacflDrvsMOfi 



u. 

-J 
u 

Q 



MACH NUMBER 



20.000 



DELBF CDEGD 

-25 25 




COFIGURATICN 




BASELINE CR8ITEP. VEHICLE 


REFERENCE DIrENSIONS 




CENTER Of GRAVITY XO - FS 107S.7 IN. 


MINO *F£A SW - 2690.00 


sQ.rr. 


.OR TO - BL 0.0 IN. 


WIND SPfiH BW • 78.055 


FT. 


MOrENT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB ■ 1290.3 


[N. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELBF (DEG) 


A 


8 


c 





E 


F 


G 


H 






BCOY 


FLAP LIFT F 


ORCE INCSEM 


■M 






-11.700 


0.0 


-0.00067 


-0.00130 


-0.00185 


-0.002H0 


-0.00342 


-0.00470 


-0.00613 


-5.000 


0.0 


-0.00015 


-0 . 00042 


-0.00086 


-0.00135 


-0.00203 


-0 . 00278 


-0.0035H 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.0 


-0.00023 


0.0 


0.00104 


0.00215 


0.00349 


0.00496 


0.00638 


10.000 


0.0 


-0.00064 


0.0 


0.00227 


0.00496 


0.00783 


0.01062 


0.01298 


16.300 


0.0 


-0.00098 


0.0 


0.00359 


0.00780 


0.01245 


0.01710 


0.02111 


22.500 


0.0 


-0.00104 


0.0 


0.00327 


0.00830 


0.01550 


0.02270 


0.02894 



ENG1NE£R_U>mX 

date 3rL*5i-">* 



FIGURE 4.1.2.1-62 

EFFECT OF BODY FLAP 



4.1.2.1-65 



c 



C72-SH..CC6C 1M 



4* 



Rockwell International 

Spec* CtvMion 



J_ *•- 



MACH NUMBER 



20.000 



LL 

a 
_j 
o 
o 



.03 



.06 



.OH 



.02 



.02 



-.04 



1 r- r | | | I | | | ! I | I '| 



I I 



I I I I 



_L_J_J_J_ 



1 (T 



XX 



DELBF CDEG) 

-55 25 

I i i i ■ I i i i : t 

i i i i i i i i rn r~i r~ri r~r 




_L.I„ 1-1. 



i i i i 



i i i i 



=**=£*; 



10 



15 



20 



30 

ALPHA 



35 

CDEG 3 



H0 






50 



55 



CONFIGURATION 




BASELINE GR9ITER VEHICLE 


REFERENCE DlftNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


U1NG AREA SU - 2690-00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BW • 78.056 


FT. 


KJtNT REFERENCE ZO - W. 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




9COY LENGTH LB - 1290.3 


IN. 











ALPHA 


(C€G) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


CELSF fCEG) 


F 


G 


H 


I 


J 


K 


L 


M 






BCOY 


FLAP LIFT F 


CRCE INCREM 


ENT 






-11.700 


-0.00342 


-0.00470 


-0.00613 


-0.00790 


-0.01075 


-0.01360 


-0.01577 


-0.01750 


-5.000 


-0.00203 


-0.00278 


-0.00354 


-0.00436 


-0.00542 


-0.00637 


-0.00693 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00349 


0.00496 


0.00638 


0.00723 


0.00763 


0.00771 


0.00737 


0.00697 


10.000 


0.00783 


0.01062 


0.01293 


0.01481 


0.01631 


0.01659 


0.01526 


0.01375 


16.300 


0.01245 


0.01710 


0.02111 


0.024M0 


0.02623 


0.02550 


0.02459 


0.02070 


22.500 


0.01550 


0.02270 


0.02994 


0.03390 


. 03446 


0.03230 


0.02794 


0.02120 



ENG 1 NEER _J*"*"J- 

date ?Z-I€e}78 



FIGURE 4.1.2.1-63 

EFFECT OF BODY FLAP 



4.1.2.1-66 



SE? 



/2-SH-CCCC IM 



'1* 



Rockwell International 

Spsc*OtvWon 



VBAR 



0.005 



DELBF CDEG) 

-25 25 



CD 

— i 

o 
a 




30 35 40 

ALPHA CDEG] 



45 



50 



CONFIGURATION 




BASEL1N£ OHU1TEH VEHICLE 


FtFtRENCE DIrtJ6JCN5 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


MING AREA SW « 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 9W - 78.055 


FT. 


MCfrtNT REFERENCE 20 - W. 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 





ALPHA (DEG) 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


DELBF (DEG) 


A 


B 


C 





E 


F 


G 






BOOYFLA 


P LIFT INCR 


D-CNT 






-11.700 


-0.00470 


-0.00613 


-0.00790 


-0.01075 


-0.01360 


-0.01577 


-0.01750 


-5.000 


-0.00278 


-0.00354 


-0.0043S 


-0.00542 


-0.00637 


-0.00693 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00496 


0.00638 


0.00723 


0.00763 


0.00771 


0.00737 


0.00697 


10.000 


0.01062 


0.01293 


0.01481 


0.01631 


0.01659 


0.01525 


0.01376 


16.300 


0.01710 


0.02111 


0.02440 


0.C2623 


0.02650 


0.02459 


0.02070 


22.500 


0.02270 


0.02694 


0.03390 


0.03*46 


0.03230 


0.02794 


0.02120 



ENGINEER 
DATE ; 



FIGURE 4.1.2.1-64 

EFFECT OF BCQYFLAP 



4.1.2.1-67 



5 



C72-SH-CCCC 1M 



'i* 



Rockwell International 

SpacvDtvtaaan 



0.080 



DELBF CDEGD 

25 



c 

o 




-.01 



20 



r 



30 35 40 

ALPHA CDEG) 



45 



50 



55 



CCf>T I GURATION 



BASELINE ORBITER *»EHIC1_E 
CENTER OF GRAVITY XD • FS 1076.7 IN. 
CR YO • 8L 0.0 IN. 

tt>£NT REFERENCE ZO - >C 375.0 IN. 



REFERENCE 0!^£NSIG^6 
WING AREA SU - 2690.00 SQ.FT. 
kING SPAN BW « 78.055 FT. 
r.A.C. CW - 39.560 FT. 

BOOY LENGTH LB - 1290.3 IN. 









ALPHA (DEG1 









20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


CELBF (CCG) 


A 


B 


C 


D 


E 


F 


G 






BGCYFLAP LIFT INCR 


E>ENT 






-11.700 


-0.00470 


-0.00613 


-0.00790 


-0.01075 


-0.01360 


-0.01577 


-0.01750 


-5.000 


-0.00278 


-0.0035* 


-0.00436 


-0.00542 


-0.00637 


-0.00693 


-0.00721 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


5.000 


0.00496 


0.00638 


0.00723 


0.007E3 


0.00771 


0.00737 


0.00697 


10.000 


0.01052 


0.01298 


0.01481 


0.01B3! 


0.01E59 


0.01525 


0.01376 


15.300 


0.01710 


0.02111 


0.02440 


0.02S23 


0.02650 


0.02459 


. 02070 


22.500 


0.02270 


0.02894 


. 033S0 


0.034146 


0.03230 


0.02794 


0.02120 



ENGINEER 
DATE " 



FIGURE 4.1.2.1-65 
EFFECT OF BODYFLAP 



4.1.2.1-63 



£C72-CH-OC-:C 1M 



#1% 



Rockwell International 

Sp*c*Div«ion 



ALTITUDE CFT. D = 300,000 to 600, 000 



DELB r CDEG) 

15 25 

f I ' I = I ' ' ' ' 



u. 

CD 




-.01 



.02 



I I 1 I 



J_1_J_ 



-L. - 1. 



^5FVr-~4---/-- -- 



>c 



i i i i ' i i i i 



'''' 



J L-J. 




1 I 1 i 



15 



20 



30 35 W 

ALPHA CDEG] 



45 



50 



CONFIGURATION 



BASELINE CRSITER VEHICLE 

CENTER OF GRAViTY XD - FS 1075.7 IN. 

OR VO - BL 0.0 IN. 

KTENT REFERENCE ZO - W_ 375.0 IN. 



RtrERENCE DirENSIONS 
WIN: AREA SW - 2690.00 SQ.FT. 
WIK> SPAN BW - 78.056 FT. 
M.A C. CW - 39.550 FT. 

3CC LENGTH LB « 1290.3 IN. 





ALPHA <D£G> 




20.000 


25.0C3 


30.000 


35.000 


40.000 


45.000 


50.000 


OELBF (DEG) 


A 


8 


C 


D 


E 


F 









90OYFLAP LIFT 1NCR 


E>£NT 






-11.700 


-0.00470 


-0.00613 


-0 . 00790 


-0.C1075 


-0.01350 


-0.01577 


-0.01750 


-5.000 


-0.00278 


-0.0035- 


-0.00435 


-0.00542 


-0.00637 


-0.00693 


-0.0072! 


0.0 


0.0 


0.0 


0.0 


O.C 


0.0 


0.0 


0.0 


5.000 


0.00496 


0.00633 


0.00723 


0.:T763 


0.00771 


0.00737 


0.006S7 


10.000 


0.01062 


0.01293 


0.01^81 


0.:i631 


0.01659 


0.01526 


0.01376 


15.300 


0.01710 


0.0211! 


0.02440 


0.:^S23 


0.02550 


0.02459 


0.02070 


22.500 


0.022T! 


C.0289-> 


0.03390 


C.:3446 


0.03230 


0.02794 


0.02120 



ENGINEER 
OATE I 



FIGURE 4.1.2.1- 66 

EFF ECT 3 C BCDYF--' 3 



4.1.2.1-69 



f E72-SH-C-.CO 1M 



'1* 



Rockwell International 

SpacaOMsion 



MACH NUMBER 



.0.250 







-.02 



-.04 



-.06 



-.08 



-10 



J_J_ 



i I i I 



I 1 1 I 



I I I I 



I I I 



s— >~ J 



L,l 1 



T I I I 



0ELS6. CDEG) 

50 100 

i l i . | I I I I | 



:S5iE 




_L_L 



1 I I i 



T I I I 




1 I I 



Mi! 



i I I I 



10 

ALPHA 



15 

CDEGD 



so 



71 M 



111 1 



30 



CONFIGURATION 




BASELINE CRBITER VEHICLE 


REFERENCE OireNSIONS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


WING AREA 34 - 2690.00 


SO. FT. 


OR TO - a. 0.0 IN. 


WING SPAN BW ■ 78.056 
M.A.C. CM - 39.560 


FT. 

FT. 


MOENT REFERENCE ZO - U. 375.0 IN. 




BCOY LENGTH L9 - 1290.3 


IN. 











ALPHA 


CDEGl 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


0EL53 (DEG) 


A 


8 


c 





E 


F 


G 


H ' 






SPEED 


BRAKE LIFT 


FORCE INCRE1 


MENT 






0.0 


0.00600 


0.00852 


0.00970 


0.00885 


0.00800 


0.00800 


0.00800 


. 00750 


15.000 


0.00400 


0.00400 


0.00400 


0.00400 


0.00400 


0.00400 


0.0O4C0 


0.00400 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0. 00400 


-0.00450 


-0.00500 


-0.00550 


-0.00600 


-0.00600 


-0.00600 


-0.00700 


45.000 


-0.00780 


-0.00890 


-0.01000 


-0.01110 


-0.01220 


-0.01275 


-0.01330 


-0.01400 


55.000 


-0.01150 


-0.01327 


-0.01490 


-0.01630 


-0.01770 


-0.01910 


-0.02050 


-0.02270 


70.000 


-0.01470 


-0.01957 


-0.02350 


-0.02600 


-0.02950 


-0.03192 


-0.0354C 


-0 . 03890 


87.200 


-0.01690 


-0.02374 


-0.03C20 


-0 . 03630 


-0.04200 


-0.04710 


-0 . 05200 


-0.05680 



ENGINEER 
DATE 






FIGURE 4.1.2.1-67 

EFFECT OF SPEEDBRAKE 



4.1.2.1-70 



£C72-Sl"i-CCCC 1M 



* 



Rockwell International 

SpacaOmon 



u 



MACH NUMBER 



0.400 



.02- 



i I i i r~i n - 1 r 



DELSB COEG) 

50 100 

I I I | I I i ' 



CD 



-.02 



-.OH 



-.06 



-.08 



_LJ_ 



J I 



J_J_L. 



I I I I iTl 




I I ! 



I I i 



I l l I I I I 



I I ! 



-10 



10 

ALPHA 



15 
CDEGD 



so 



as 



30 



35 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER Cf GRAVITY XO - FS 107S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO - a. 0.0 IN. 


WING SPAN BW » 78.055 


FT. 


MCfOn REFERENCE 20 - W. 375.0 IN. 


M.A.C. CM - 39.550 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.'000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELSB (OEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEEE 


6RAKE LIFT 


FORCE INCRE1 


JCNT 






0.0 


0.00500 


0.00852 


0.00970 


0.00885 


0.00800 


0.00800 


0.00800 


0.00750 


15.000 


0.00400 


0.00400 


0.0O400 


0.00400 


0.00400 


0.00400 


0.00400 


0.00400 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00400 


-0 . 00450 


-C . 00500 


-0.00550 


-0.00600 


-0-00600 


-0.00600 


-0 . 00700 


45.000 


-0.007B0 


-0 . 00890 


-0.01000 


-0.01110 


-0.01220 


-0.01275 


-0.01330 


-0.01400 


55.000 


-0.01150 


-0.01327 


-0.01490 


-0.01630 


-0.01770 


-0.01910 


-0.02050 


-0.02270 


70.000 


-0.01470 


-0.01957 


-C . 02350 


-0.02500 


-0.02850 


-0.03192 


-0.03540 


-0.03890 


07.200 


-0.01690 


-C . 02374 


-0 . 03020 


-0 03530 


-0.04200 


-0.04710 


-0 . 05200 


-0.05580 



ENGINEER I6£? 
0ATE„.5rl2.-^5 



FIGURE 4.1.2.1-68 

EFFECT OF SPEEDBRAKE 



U. 1.2. 1-71 



£C72-Sh-CCeQ 1M 



* 



Rockwell International 

Spaca Dlvaion 



r 



MACH NUMBER 



DELSB CDEGD 

50 100 

t — r 



CD 




%? 



CCNFIGtRATION 



BASELINE ORSITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN. 

Cfl YC - BL 0.0 IN. 

MCt^NT REFERENCE ZO « W. 375.0 IN. 



DN 

REFERENCE DIMENSIONS 




WING AREA SW • 2690.00 


SQ.FT. 


WING SPAN BM - 73.056 


F7. 


M.A.C. CW - 39.550 


FT. 


BODY LENGTH LB - 1290. J 


IN. 











ALPHA 


(DEG) 






— — ■ — 


-10.000 


-5.000 


0.0 


5.0C0 


10.000 


15.000 


20.000 


25.000 


CELS3 (CEG) 


A 


B 


c 


D 


E 


F 


G 


H 






SPEEC 


BRAKE LIFT 


FORCE INCRE 


f€NT 






0.0 


0.00850 


0.00S25 


0.01000 


0.01000 


0.00950 


0.00900 


0.0065C 


0.00300 


15.000 


0.00588 


. 00544 


0.00500 


0.00450 


0.00450 


0.00500 


0.00550 


. 00500 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00350 


-0.00349 


-0.00639 


-0.00567 


-0.00592 


-0.00425 


-0.00500 


-0.00400 


45.000 


-0.00700 


-0 . 0C863 


-0.01259 


-0.01167 


-0.01209 


-0.00997 


-0 . 00950 


-0.O1C00 


55.000 


-0.01196 


-0.01539 


-0.01S82 


-0.01BOO 


-0.01850 


-0.01742 


-0.01634 


-0.01525 


70.000 


-0.0172M 


-0.02235 


-0.02746 


-0.02935 


-0.03000 


-0.02S00 


-0.02800 


-0.02700 


67.200 


-0.02307 


-0.03009 


-0.03711 


-0.04107 


-0.04400 


-0.04833 


-0.05256 


-0.05599 



ENGINEER 3>?i^ 
DATE.._1;I5rJ2g; 



FIGURE 4.1.2.1-69 

EFFECT OF SPEEDBRAKE 



4.1.2.1-72 



£C72-s::-coeo im 



4> 



Rockwell International 

Space Division 



L 



MACH NUMBER = 0.800 

,18 l i M I | I I l" I I I ! ll 



DELSB CDEGD 

50 100 



CD 
■■A 



.OS 1 - 



I I I 



J... I...I ! 



i ' I 



I I III 




I I I 



IT I 



I ! 1,1 



J_L 



I I I 



TTT 



I I I i 



J_L 



I I 1 



I 1 



-10 



10 15 

ALPHA CDEGD 



so 



25 



30 



35 



COFIGURAl 
BASELINE CR9ITER VEHICLE 


new 




• HEFEHENCE DIMENSIONS 


CENTER CF GRAVITY XO - FS 1076.7 IN. 


WING AREA SW • 3690.00 


SQ.FT. 


CR YO - 8L 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MOMENT REFERENCE 20 - W. 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BCOY LENGTH LB « 1290. J 


IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELSB (CGG) 


A 


B 


c 


D 


E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCRE 


"€NT 






0.0 


0.01000 


0.01000 


0.01000 


O.0I00O 


0.01100 


0.01100 


0.01100 


0. 01100 


15.000 


0.00500 


0.00500 


0.00500 


. 00450 


0.00550 


0.00550 


0.00S50 


0.00550 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00591 


-0.00654 


-0 . 00727 


-0.00S39 


-0.00559 


-0.00556 


-0.00553 


-0.C0558 


45.000 


-0.01159 


-0.01361 


-0.01563 


-0.01325 


-0.01194 


-0.01203 


-0.01212 


-0.01221 


55.000 


-0.01778 


-0.02m 


-0.02450 


-0 . 02058 


-0.01950 


-0.02000 


-0.02050 


-0.02100 


70.000 


-0 . Q3349 


-0 ^34 74 


-0.03599 


-0.03507 


-0.03200 


-0.03383 


-0.03566 


-0.03749 


87.200 


-0 . 04753 


-0 . 04898 


-0 . 05039 


-0 . 05028 


-0.04850 


-0.0527! 


-0.C5S92 


-0.06113 



ENGINEER I&t^ 
OATE *V' "S>-~?£> 



FIGURE 4.1.2.1-70 
EFFECT OF SPEEDBR--.KE 



4.1.2.1-73 



5? P -: 



c "52-SH-CCeO IM 



* 



Rockwell International 

SpacaDlviMon 



MACH NUMBER 



0.900 



.03 



DELSB CDEGD 

50 100 

I I I I | I I I I 



"SES 



C/5 



-.02 



-.04 



-.06 



.08 

-10 



.!, ! 1 -1. 



I I I 1 



-LI 1 I 



i I i I 



I I I T 



1 I I I 



1. 1, ! 



I I I 




I I I l 



I 1 



i I l" 



1 I 



1 IT 



10 

ALPHA 



15 

CDEGD 



20 



30 



35 



CONFIGURATION 




BASELINE 0R81TER VEHICLE 


REFERENCE DIMENSIONS 




COLTER OF GRAVITY XO - FS 1075.7 IN. 


WIND AREA SW - 2590.00 


SQ.FT. 


OR YO - 8L 0.0 IN. 


WING SPAN BW • 78.055 


FT. 


fCrCNT REFERENCE 20 - U. 375.0 IN. 


M.A.C. CW - 39.550 


FT. 




BODY LENGTH LS - 1290.7 


IN. 











ALPHA 


(DEG1 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELS3 (OEGi 


A 


B 


C 





E 


F 


G 


H 










FORCE INCRFJ 


»€NT 






fartiD 


BRAKE LIFT 


0.0 


0.01000 


0.01000 


0.01000 


0.01050 


0.01250 


0.01100 


0.00950 


0.00800 


15.000 


0.00550 


0.00550 


0.00550 


0.00550 


0.00600 


0.00550 


0.00500 


0.00450 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0 . 00924 


-0.00904 


-0.0C8B5 


-0.00785 


-0.00648 


-0.00530 


-0.00412 


-0.00294 


45.000 


-0.02019 


-0.01924 


-0.01829 


-0.01633 


-0.01380 


-0.01187 


-0.00993 


-0.008C0 


55.000 


-0.03200 


-0 . 03000 


-0.02800 


-0.02500 


-0 . 02200 


-0.02000 


-0.01800 


-0.01600 


70.000 


-0.04150 


-0.04100 


-0.04050 


-0.03800 


-0.03550 


-0.03250 


-0.02950 


-0 . 02550 


87.200 


-0.04500 


-0 . 05000 


-0.05500 


-0 . 05500 


-0 . 05400 


-0.05000 


-0 . 046C0 


-0.0420C 



ENGINEER _~>£»fi a 
OATE__3£3L-:ig> 



FIGURE 4.1.2.1-71 

U- L bUT OF SPEEDBRAKE 



4.1.2.1-74 



S;L ,1-L 



Cl CO IM 



*> 



Rockwell International 

SpacaOIVMion 



MACH NUMBER 



0.950 



DELSB CDEG] 

50 100 



CD 

a 






CCnFIGLRaT 


BASELINE OR 


ITER VEHICLE 


CENTER Of" GRAVIT. 


XO - FS 076.7 IN. 


OR 


YO • BL 0.0 IN. 


tt>ENT REFERENT 


20 • WL 375. n IN. 



TICN 




REFERENCE 0I^EN3ICNS 




WING AREA SW « 2S90.00 


SQ.FT. 


HINT. SPAN BW - 78.056 


FT. 


M.A.C. CW • 39.560 


FT. 


BCO v LENGTH LB - 1290.7 


IN. 



CCLS8 (CEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70 . 000 
87.200 



■10.000 
A 



-5.000 
B 



ALPHA (C€G) 



0.0 
C 



5.000 




10.000 
E 



15.000 

F 



20.000 
G 



25.000 
H 



0.01000 
. 00S30 
0.0 
-0.00892 

-o.oism 

-0.02750 
-0.04000 
-0 . 05650 



0.01000 
. 00630 
0.0 
-0.00892 

-o.oiam 

-0 . 02750 
-0 . 04000 

-0 15650 



SPEEOeRAKE LIFT FORCE INCREMENT 



0.01000 
0.00630 
0.0 

-O.O0S92 

-o.oism 

-C . 02750 
-0.04000 
-0 . 05650 



0.01000 
0.00500 
0.0 

-0.00517 
-0.01192 
-0.02100 
-0 . 03650 
-0 15650 



0.01250 
0.00600 
0.0 

-0.00679 

-0.01444 

-0.02300 
-0.03750 
-0.05550 



0.01100 
0.00500 
0.0 
-0.00546 
-0.01198 
-0.01950 
-0.03150 
-0.04650 



0.00950 
0.00400 
0.0 
-0.00414 

-0.0C952 
-0.01600 
-0.02550 
-0 . 03650 



0.00800 
0.00300 
0.0 

-0.00282 
-0.00706 
-0.01250 
-0.01950 
-0.02650 



1 



ENGINEER l^*^ 
DATE„^;[3ti35I 



FICJRE 4.1.2.1-72 

EFFECT OF 5PEEDBRAKE 



4.1.2.1-75 



S D 7 :■: - S H - C C L 1 M 



^ 



Rockwell International 

Space Dtvwon 



MACH NUMBER 



0.980 



OELSB CDEG) 

50 1 00 



CD 




-.08 



CENTER OF GRAVITY XO 
OR YO 

rCT-CNT REFERENCE Z 



CONFIGURATION 




* VEHICLE . 


REFERENCE DlfCNSICNS 




3 - FS 1076.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


3 - a. o.o in. 


WING SPAN BW - 78.055 


FT. 


« W. 375.0 IN. 


M.A.C. CW ■ 39.560 


FT. 




BCOY LENGTH LB - 1390.3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.C 1 


0.0 


5.000 


10.000 


15.000 


Z .000 


25.000 


DELSB <0EG) 


A 


8 


C 





E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCREI 


'ENT 






0.0 


0.01000 


0.01000 


0.01000 


0.01000 


0. 012*3 


0.01100 


0.00957 


0.00813 


15.000 


0.00623 


0.00623 


0.00623 


0.00H86 


0.00591 


0.00*82 


0.00390 


0.00311 


35.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00835 


-o.ooe-H 


-0.00852 


-0.00503 


-0.00671 


-0.005*2 


-0. 00W17 


-0.00290 


H5.000 


-0.01668 


-o.oi7r4 


-0.01736 


-0.01160 


-o.o mas 


-0.01179 


-0.00936 


-0.00690 


55.000 


-0.02HSM 


-0. 025-8 


-0.02637 


-0.020H6 


-0.02267 


-0.01901 


-C. 015*0 


-0.0I17W 


70.000 


-0.03838 


-0.03&-2 


-0.03882 


-0.03577 


-0.C3581 


-0.03063 


-0.0237* 


-0.01707 


87.200 


-0.05613 


-0.055^9 


-0 . 05503 


-0.05551 


-0.C5555 


-0.0**59 


-0.03289 


-0.0213H 



ENGINEER >lJ£xl} 
DATE ScIgSg 



FIGUR: 4.1.2.1-73 

r FFECT OF SPEEDBRAKE 



*. 1.2. 1-76 



SD",2>SH-CCCO IM 



#JI 



Rockwell International 

SpacaDhflMon 



MACH NUMBER 



1.050 



DELSB CDEG: 

50 100 



.02 



CD 
en 



-.06 



-.08 



■10 



n^r 



1_1, MM-M I M M 



I I I I 



TTTT 




i I ) i ) I 



I I I > 



TTT 



MM 



i I i I I 



J I ,1.1 



10 IS 

ALPHA CDEG] 



SO 



30 



CO>f IGURATION 




BASELINE 0F<3ITER VEHICLE 


REFERENCE OII-ENSICNS 




CENTER OF GRAVITY XO - FS 107S.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


OR Y0 - BL 0.0 IN. 


WING SPAN BW • 7B.055 


FT. 


MOftNT REFERENCE 20 - WL T75.0 IN. 


M.A.C. CU - 39.550 


FT. 




BOOY LENGTH LB ■ 1290.7 


IN. 











ALPHA 


<0EG> 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


OELSS (OEGJ 


A 


B 


C 





E 


F 


G 


H 










FORCE INCRE1 


*ENT 






c^t£0 


BRAKE LIFT 


0.0 


0.01000 


0.01000 


0.01000 


0.01000 


0.01214 


0.01100 


0.00966 


0.00871 


15.000 


0.00481 


0.00494 


. 00507 


0.00480 


0.00546 


0.00458 


0.00403 


0.00339 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00582 


-0.0061S 


-0.00653 


-0.00597 


-0.00509 


-0.00521 


-0.00432 


-0.00344 


45.000 


-0.01243 


-0.01307 


-0.01385 


-0.01311 


-0.012S4 


-0.01103 


-0.00920 


-0.00739 


55.000 


-0.01921 


-0.02093 


-0.02179 


-0.02122 


-0.02048 


-0.01747 


-0.01444 


-0.01143 


70.000 


-0.03239 


-0.03327 


-0.03420 


-0.03447 


-0.03379 


-0.02789 


-0.02128 


-0.01498 


87.200 


-0.05040 


-0 . 05058 


-0 . 05077 


-0.05179 


-C.05'.79 


-0.04072 


-0.02920 


-0.01783 



ENGINEER ^&£> 



FIGURE 4.1.2.1- 74 

EFFECT OF SPEEOBSA- 



4.1.2.1-77 



5? n -r 



D72-SH-CCCO IM 



e 



Rockwell International 

Seac*OrmKt\ 



MACH NUMBER = 1.100 

•°^i « i n n r - ! - ] m r~ ] r~n r~r~i n r~ r~~i r~r 



DELSB CDEG) 

50 lQQ 



m 

8 



.06 



1111 




till 



X 



I ! I J., 



T i I i 



till 



1111 



i i r 



III! 



1 I ' 



-10 



10 

ALPHA 



15 

CDEG) 



20 



25 

a 



30 



35 



COFIGLRATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE OICENSICNS 




CENTER Of GRAVITY XO ■ FS 1076.7 IN. 


WING AREA SW • 3690.00 


SQ.FT. 


CR TO - BL CO IN. 


WING SPAN BW « 7S.055 


FT. 


MOENT REFERENCE ZO - WL 375.0 IN. 


M.A.C. CW • 39.560 


FT. 




BCOY LENGTH LB - 1290. J 


IN. 











ALPHA 


(CEG) 








-10.000 


-5.300 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DELS8 <0EG) 


A 


8 


C 


o 


E 


F 


G 


H 






SPEEC 


6RAKE LIFT 


FORCE INCRE 


rENT 






CO 


0.01000 


0.01000 


0.01000 


0.01000 


0.01200 


0.01100 


0.01000 


0.00900 


15.000 


C 00441 


0.00455 


0.00458 


0.00482 


0.00526 


CC0470 


0.00415 


0.00359 


25.000 


0.0 


CO 


0.0 


0.0 


CO 


0.0 


0.0 


0.0 


35.000 


-0.00474 


-0.00519 


-0.00565 


-0.00618 


-0.00582 


-0.00510 


-0.00438 


-0.00366 


45.000 


-0.00998 


-0.01109 


-0.01220 


-0.01335 


-0.01224 


-0.01061 


-C00S97 


-0.00733 


55.000 


-0.01654 


-0.01802 


-0.01950 


-0.02100 


-0.01950 


-0.01655 


-0.01360 


-0.01065 


70.000 


-0.02943 


-0.03062 


-0.03180 


-0.03334 


-0.03214 


-0.02631 


-0.02048 


-0.01465 


87.200 


-COM 800 


-0.04800 


-0.04800 


-0 . 04900 


-0 . C4900 


-0.03872 


-0 . 02944 


-0.01615 



ENGINEER 1£*D 
DATE„ .1:1X^1 



FIGURE 4.1.2.1-75 

EFFECT OF SPEEDBRAKE 



4.1.2.1-78 



<s n *r 



D 



/2 



3H-ccec 1M 



€* 



Rockwell International 

Spac*OtvMon 



r 



k*.:h number 



1.200 



DELSB CDEG) 

50 100 




CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCE DIMENSIONS 




CENTER Cf GRAVITY XO • FS 1076.7 IN. 


WING AREA SW - 2590.00 


SQ.FT. 


CR YO » BL 0.0 IN. 


WIND SPAN BW ■ 78.056 
M.A.C. C-l - 39.560 


FT. 
FT. 


K>£NT REFERENCE ZO - W. 375.0 IN. 




BOOY LENGTH LB - 1290.3 


IN. 











ALPHA 


CDEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


DEL5B (CEG) 


A 


B 


C 


D 


E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCRE1 


^OfT 






0.0 


0.01200 


0.01100 


0.01000 


0.01000 


0.01200 


0.01100 


0.01000 


0.00900 


15.000 


0.00650 


0.00600 


0.00550 


0.00500 


0.00550 


0.00500 


0.00450 


0.00400 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00951 


-0.00809 


-0.00667 


-0.00551 


-0.00587 


-0.00500 


-0.00413 


-0.00327 


45.000 


-0.01744 


-0.01539 


-0.01333 


-0.01167 


-0.01245 


-0.01009 


-0.00773 


-0.00537 


55.000 


-0.02400 


-0.02200 


-0.02000 


-0.01850 


-0.01945 


-0.01550 


-0.01155 


-0.00760 


70.000 


-0.03500 


-0.03300 


-0.03100 


-0 . 03000 


-0.03000 


-0.02550 


-0.02100 


-0.01650 


87.200 


-0.04700 


-0.04500 


-0.04300 


-0.04300 


-0.043CO 


-0 . 03700 


-0.0310C 


-0.02500 



ENGINEER ££*D 
0ATE„3rI5£g 



FIGURE 4.1.2.1-76 

EFFECT OF SPEED8RAK; 



k 1.2.1-79 



SD 72 -SH-CCiO 1M 



i 



'J* 



Rockwell International 

SpaeaOivsicn 



MACH NUMBER 



i.300 



DELSB CDEGD 

50 100 

| I I I I 



-.02 



CD 

in 




BASELIhE ORSITTR VEHICLE 

■CENTER Of" GRAVITY XO ■ FS 1075.7 IN. 

OR YO ■ BL 0.0 IN. 

MCf-tNT REFERENCE ZO » WL 375.0 IN. 



TION 




REFERENCE DIMENSIONS 




WING AREA SW » 2690.00 


sc.rr. 


WING SPAN SW • 78.055 


FT. 


M.A.C. CW - 39.560 


FT. 


BCOY LENGTH LB ■ 1290 3 


IN. 











ALPHA 


(OEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20 . 000 


25.000 


DELSB (DEG! 


A 


B 


c 





E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCRE 


*ENT 






0.0 


0.01100 


0.01052 


0.01000 


0.00950 


0.01100 


0.01100 


O.OUOO 


0.01100 


15.000 


0.00492 


0.00483 


0.00475 


0.00505 


0.00526 


0.00506 


0.00480 


0.00450 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00817 


-0.00704 


-0.00592 


-0.00503 


-0 . 00525 


-0.0C500 


-0.00475 


-0.00451 


45.000 


-0.0t515 


-0.01369 


-0.01223 


-0.01057 


-0.01109 


-0.01005 


-0.00902 


-0.00799 


55.000 


-0.02125 


-0.02000 


-0.01875 


-0.01685 


-0.01747 


-0.01531 


-0.01315 


-0.01100 


70.000 


-0.03051 


-0.02950 


-0.02849 


-0. 02754 


-0.02725 


-0.02475 


-0.02225 


-0.01975 


87.200 


-0.04200 


-0.04100 


-0 . 03973 


-0.04034 


-0.03971 


-0 . 03544 


-0.03112 


-0.02583 



ENGINEER _ ,. 



FIGURE 4.1.2.1-77 

EFFECT OF SPEEDBRAKE 



4.1.2.1-80 



SD72-SH-CCCC I M 



* 



Rockwell International 

SpacaOMnon 



L 



r.vCH NUMBER 



1.500 



DEL SB CDEG: 

50 100 

I I I | I I I I | 



j 



-.06 




P 13 

ALPHA CDEGD 



CONFIGURATION 


BASELINE CR9ITER \EHICLE 


REFERENCE DIMENSIONS 


CENTER OF" GRAV! 'Y XO - FS 1076.7 [N. 


WING AREA SU ■ 2630.00 SQ.FT. 


OR YO « 9L 0.0 IN. 


WING SPAN BW ■ 78.056 FT. 


M>ENT REFERENC" ZO - W. 375.0 IN. 


M.A.C. CW - 39.560 FT. 




BODY LENGTH LB - 1290.3 IN. 











ALPHA 


(OEG) 










-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


23.00C 


25.000 


CG.SB <C£G) 


A 


8 


c 


D 


E 


F 


G 


H 






SPEE-i 


8RAKE LIFT 


FORCE INCREI 


h€NT 






0.0 


0.00915 


.00946 


. 0096C 


. 00855 


0.00925 


0.01053 


0.31154 


0.01270 


15.000 


0.00305 


-.00343 


0.0037!:- 


0.00477 


0.00468 


0.00477 


. 30483 


0.00485 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00619 


-0.00557 


-0.00476 


-0.00428 


-0.00412 


-0 . 00480 


-0 . 00525 


-0 . 00548 


H5.000 


-0.01188 


-0.01130 


-0.01030 


-0.00894 


-0.00871 


-0.0OS66 


-0.01005 


-0.01007 


55.000 


-0.01711 


-0.01552 


-0.01535 


-0.01443 


-0.01436 


-0.01455 


-0.01425 


-0.01432 


70.000 


-0.0236H 


-0.02380 


-0.02405 


-0.02404 


-0.02356 


-0.02306 


-0.C2296 


-0.02328 


87.200 


-0.03415 


-0.03433 


-0 . 03452 


-0 . 03574 


-O.C?->62 


-0.032S6 


-0.23075 


-0.02996 



ENGINEERINGS-) 

D4TE_.^S3S 



FIGURE 4.1.2.1-78 

EFFECT OF SPEEDERS E 



4.1.2.1-81 



SL 72-SK CCCC I M 



e 



Rockwell International 

SpacsDMMon 



MACH NUMBER 
.C2r-rr i i I i I i I 



m 

o 
a 




-.04 



-.06 



2.000 

l l I l l I I I I I I I I l 



DEL SB CDEG) 

50 100 

1 I i I i I i I I . I 



I I i I i I II I I II I I I i I 



_ gg , ; I I I .1 I ! I I I I I 1 I I I I I I I I 1 I ' I I I I I I I I I I I 1 I ! I I T | | | | | | | 

' -10 -5 5 10 15 20 23 30 35 HO 

ALPHA CDEG) 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE Dlt^NSIONS 




CENTER OF GRAVITY XO - FS 1075.7 IN. 


MING AREA 34 - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN ew - 78.056 


FT. 


M>£NT REFERENCE ZO - U. 375.0 IN. 


M.A.C. CU • 39.560 


FT. 




BOOY LEN3TH L9 - 1290.7 


IN. 





ALPHA (DEG) 


-10.000 


-5.000 


0.0 


5. ota 


10.000 


15.000 


20.000 


25.000 


30 . 000 


0ELS8 IOCS* 


A 


B 


C 


D 


E 


F 


G 


H 


I 








SPEEX8RAKE 


LIFT FORCE 


INCREMENT 








0,0 


0.00650 


0.00650 


0.00650 


0.00650 


- 00700 


0.00550 


0.00600 


0.00550 


. 00500 


15.000 


0.00308 


0.00302 


0.00295 


0.00283 


0.00275 


0.00279 


0.00275 


0.00271 


0.00267 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00375 


-0.00358 


-0.00342 


-0.003PS 


-0.00266 


-0.00299 


-0.00322 


-0.00345 


-0.00368 


45.000 


-0.00838 


-0.00788 


-0.00738 


-0.00658 


-0.00614 


-0.00678 


-0.00689 


-0.00700 


-0.00711 


55.000 


-0.01293 


-0.01227 


-0.01161 


-0.01095 


-0.01100 


-0.01104 


-0.01100 


-0.01095 


-0.01092 


70.000 


-0.01800 


-0.01BOO 


-0.01800 


-0.01900 


-0.01900 


-0.01745 


-0.01800 


-0.01955 


-0.01910 


B7.200 


-0 . 02700 


-0.02700 


-0.02700 


-0 . 02700 


-0.0270G 


-0 . 02750 


-0 . 02792 


-0 . 02934 


-0 . C2976 



r 



ENGINEER I& O 



FIGURE 4.1.2.1-79 

EFFECT OF SPEEDBRAKE 



4.1.2.1-82 



'1* 



Rockwell International 

Spac*Ctv«ion 



CD 



MAC- NUMBER 



3.000 



DELSB COEG) 

50 100 

| I i I I | I I 



-.02- 




- . 0- r 



-.06- 



CONF1GURATI0N 



BASELIfC CR ITER VEHICLF 
CENTER OF GRAVITY XO « FS H76.7 IN. 
CR YO - a. 0.0 IN. 

f-O-ENT REFERENCE ZO - U. 375.0 IN. 



REFERENCE OlfCNSICNS 
WING AREA SW - 2690.00 SQ.FT. 
WING SPAN BW - 78.055 FT. 
M.A.C. CW • 39.560 FT. 

BODY LENGTH LB « 1590.3 IN. 











ALPHA 


(OEG) 








-10.000 


5.000 


0.0 


5. COO 


10.000 


15.000 


20.000 


25.000 


CELS8 CDEG) 


A 


8 


c 


C 


E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCRE1 


"ENT 






0.0 


0.0080S 


C 10782 


0.00755 


0.0C728 


0.00717 


0.00712 


0.00648 


0.00533 


15.000 


0.00323 


0.00313 


. C0302 


0.00291 


0.00287 


0.00285 


0.00259 


0.00213 


25.000 


CO 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00355 


-0 00336 


-0.00318 


-0.00300 


-0.00296 


-0.00302 


-0.00275 


-0.00223 


i*5. 0C0 


-0 . 0C555 


-C.CC557 


-0.00559 


-0.00550 


-0.00548 


-0.00526 


-0.00479 


-0.00402 


55.000 


-0.00688 


-0.00724 


-0.00750 


-0.00796 


-0.00774 


-0.00702 


-0.00S40 


-0.00555 


70.00C 


-0.01000 


-0 01100 


-0.01300 


-0.0.313 


-0.01278 


-0.01301 


-0.01112 


-0.00950 


87.200 


-0.01487 


-0 31692 


-0.CI897 


-0.0=102 


-0.02152 


-0 . 02232 


-0.01855 


-0.01550 



ENGINEER^, ^ 
DATE *vi225£ 



FIG 'RE 4.1.2.1-80 

EFFECT OF SPEEDERAKE 



4.1.2.1-83 



L 



7 2-SH-CCeO IM 



#J> 



Rockwell International 

SpecaOMvcn 



liACH NUMBER 
•°gr ; , , | I i , 



3.000 



DELSB CDEG: 

50 100 



CD 
tn 

_i 




-.04 



.05 



.08 



jl t .: 



i i i i I i i i i 



I > I i 



TT 



l 1 I I I I ' 



I i I I 

III: 



15 



20 



30 35 HO 

ALPHA CDEGD 



-I I..-I L_ _[ I i I i i i 

45 50 



COflGURATION 




fcWstLIri. ORBITER vEHJCli. 


HJ-LHLNCE DirENSICN5 




CENTER CF GRAVITY XO - FS 10TS.7 IN. 


HIN3 AREA SW - 2590.00 


SQ.FT. 


CR YO - a. 0-0 IN. 


WING SPAN BU - 73.055 


FT. 


MOENT REFERENCE ZO - H_ T75.0 IN. 


M.A.C. CW - 39.550 


FT. 




SCOY LENGTH LB • 1290.3 


IN. 





ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


CELS8 C0EG) 


F 


G 


H 


I 


J 


K 


L 






SPEEOBRAKE 


LIFT FCRCE 


INCREfENT 




0.0 


0.00712 


0.00548 


0.00533 


0.00416 


0.00303 


0.00188 


0.00073 


15.000 


0.00295 


0.00259 


0.00213 


0.00167 


0.00121 


0.00075 


0.00029 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00302 


-0.00275 


-0.00223 


-0.00171 


-0.00119 


-0.00067 


-0.00015 


45.000 


-0.00525 


-0.00479 


-0.00402 


-0.00326 


-0.00249 


-0.00173 


-0.00096 


55.000 


-0.00702 


-0.00640 


-0.0C555 


-0.00470 


-0.00385 


-0.00300 


-0.00215 


70 . 000 


-0.01301 


-0.01112 


-0.00950 


-0.00788 


-0.00525 


-0.0C45H 


-0 . 00302 


• 87.200 


-0.02232 


-0.01866 


-0.01550 


-0.01234 


-0.00918 


-0.00602 


-0.00286 



ENGINEER 32*1^ 



FIGURE 4.1.2.1-81 

EFFECT OF SPEEOBRAKE 



4.1.2.1-34 



7 2 






CCCO 1M 



'I* 



Rockwell International 
Space Divaton 



M *.ZH NUMBER 



4.000 



DELSB CDEG) 

50 100 



CD 
V) 



■ J 




-.06 



-.'3 



I 1 I I 



I I...L 



1 I 1..I 



J l 



I ' I 



-10 



,11,1 J ,., 



I L, 



10 

ALPHA 



15 

CDEGJ 



20 



30 



35 



CONFIGURATION 



BASELINE 0R8ITER VEHICLE 

CENTER OF GRAVITY X0 - FS 10*76.7 IN. 

OR YO - a. 0.0 IN. 

;OENT REFERENCE 20 - WL 375.0 IN. 



REFERENCE Olh-ENSIONS 

WING AR£A SW - 2690.00 SQ.FT. 

WING SPAN Sw - 78.056 FT. 

M.A.C. 04 - 39.560 FT. 

BOOV LENGTH L9 ■ 1590.7 IN. 











ALPHA 


(DEG) 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CELS8 !CEG> 


A 


B 


C 





E 


F 


G 


H 






SPEED 


6RAKE LIFT 


FORCE INCRE1 


t-CNTT 






0.0 


0.00400 


0.00244 


0.00150 


0.00150 


0.00150 


0.00150 


0.00150 


0.00150 


15.000 


C. 00160 


0.00097 


. 00060 


0.00060 


0.00060 


0.00060 


0.00060 


0.00060 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00110 


-0.001 II 


-0.001 10 


-0.00105 


-0.00100 


-0.00095 


-0.00090 


-0.00090 


45.000 


-0.00160 


-0.00161 


-0.00160 


-0.00156 


-0.00150 


-0.00142 


-0.00130 


-0.00100 


55.000 


-0.00310 


-0.00316 


-0.00310 


-0.00287 


-0.00260 


-0.00230 


-0.00200 


-0.00180 


70.000 


-0.00840 


-0.00871 


-0.00840 


-0.00715 


-0.00590 


-0.00500 


-0.00410 


-0.00300 


87.200 


-0.01500 


-0.01555 


-0.01500 


-0.01280 


-0.01060 


-0.009S2 


-0.00730 


-0 . 00570 



ENGINEER J2S>S2 

DATE„.i-r-T\rns 



FIGURE 4.1, 
EFFECT 



2.1-82 

OF SPEEDBRAK' 



-.1.2.1-85 



SE 72-CH-CCCG 1M 



'J* 



Rockwell International 

Sp*c* Dwteion 



M/ CH NUMBER 



4.000 



.02 



DELS3 CDEGD 

50 100 

i i ; r 




CD 

c 
a 



.02 



.04 



-06 



t i i r 



-.08' 'I'' 
15 20 



i i i r 



I I I I i I I 



I I I I 



JLJ»ii^l w .LAjj!b . — t 



"I I "T'T 



-i-i- 1 I 1 1--1 1 I I I I I t i I i I i i I ) I i i 
25 30 35 HO 45 



i r 



I i i i 



i i i i 



ALPHA CDEGD 



50 



CONFIGURATION 




BASELINE CRBKER VEHICLE 


REFERENCE OlftNSICNS 




CENTER CF GRAVITY XO » FS 1075.7 IN. 


MING AREA SW • 2590.00 


SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BW - 78.056 


FT. 


MC*€NT REFERENCE ZO - U. 375.0 IN. 


H.A.C. Ol • 39.560 


FT. 




BCOY LENGTH LB - 1290.3 


IN. 







ALPHA (DEG) 


15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


DELS3 (DEG) 


F 


G 


H 


I 


J 


K 


L 






SPEED8RAKE 


LIF- FCRCE 


INCREPENT 






0.0 


0.00150 


0.00150 


0.00150 


0.00150 


0.00117 


0.00050 


0.0 


15.000 


. 00060 


0.00060 


0.00060 


. 00060 


0.00050 


0.00030 


0.00015 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00095 


-0.00090 


-o.oooso 


-0.00080 


-0.00050 


0.0 


0.0 


45.000 


-0.00142 


-0.00130 


-0.00100 


-0.00100 


-0.00067 


0.0 


0.0 


55.000 


-0.00230 


-0.00200 


-0.00180 


-o.ooieo 


-0.00060 


0.0 


0.0 


70.000 


-0.00500 


-0.00410 


-0.00300 


-0.00200 


-0.00100 


0.0 


0.0 


87.200 


-0.00892 


-0.00730 


-0.00570 


-0.00350 


-0.00217 


-0.00170 


0.0 



ENGI 
DATE 






FIGURE 4.1.2.1-83 

EFFECT OF SPEEDBRAKE 



U. 1.2. 1-86 



SL 72-SH-CC(:0 IM 



o 



Rockwell International 

Space Division 



L 



; J .,CH NUMBER 



5.000 



DELSB CDEG3 

50 100 



"J 



-.06 






CONFIGURATION 






BASELINE 0R8 


TER VEHICLi 


REFERENCr 


DIMENSIONS 




CDfTER OF GRAVITY 


XO - FS 1076.7 IN. 


WING AREA 


SW - 2690.00 


SQ.FT. 


CR 


YO - BL 0.0 IN. 


WIM3 SPAN 


BW « 78.056 


FT. 


M>£NT REFERENCE 


ZO ' W. 375.0 IN. 


M.A.C. 


CW - 39.560 


FT. 






BODY -ENGTH 


LB » 1290.3 


IN. 











A.PHA 


(TEG) 










-10.000 


-5.000 


0.0 


5.000 


10.300 


15.000 


20 . 000 


25.000 


DELS9 (CEG) 


A 


B 


c 





E 


F 


G 


H 






SPEED 


BRAKE LIFT 


S"0PCE 1NCREI 


*ENT 






0.0 


0.00220 


0.00247 


. 0022C 


0. J0UO 


CO 


0.0 


0.0 


0.0 


15.000 


0.00090 


0.00101 


. 0009C 


. 30045 


CO 


0.0 


0.0 


0.0 


25.000 


0.0 


O.C 


0.0 


o.: 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00080 


-0.C0082 


-0 . 0008. 


-0 10070 


-0.00060 


-0.00050 


-0.00040 


-0.00030 


45.000 


-0.00160 


-0.00165 


-0.0016C 


-0. .0140 


-0.00120 


-0.00115 


-0.00110 


-0.00060 


55.000 


-0.00260 


-O.C 0259 


-0 . 0026C 


-0. .0225 


-0.00:90 


-0.00175 


-0.00160 


-0.001C0 


70.000 


-0.00500 


-O.C 0512 


-0 . 00500 


-0 . 00456 


-0.00400 


-0.00341 


-0 . 00270 


-0.001=3 


87.200 


-0.01150 


-0.CU82 


-0.0115C 


-0 '1032 


-0.00390 


-0.00730 


-0 . 00570 


-0 . 004 1 J 



ENGINEER l££L> 

date.^ -^nczjB, 



FIGURE 4.1.2.1-84 

EF-ECT OF SPEEDBRAKE 



k. 1.2. 1-37 



£D "/2-Sh-CCeO 1M 



#11 



Rockwell International 

5pac«DiviMon 



MACH NUMBER = 

•<« i i i i ■ i i i l I I I 



5.000 



DELSB COEG) 

50 100 



.0 S 






.02 



-.04 



.06 



-.08 



r r < h 



jg ^r^ ^^" JM Uliii.tfai.ijiJ ' 1 if ni;iH t ilii '__1 ij ft '^ 'jUii 'ii'ili 'If • ■ 1 IT r H I I 



_L_L 



JL_L 



_L_L 



I I I I i i I i I i I ! 



_L_L. 



_L 



J_ 



I 1 I 



T-| I I 



i i i 



"i i i I i i r 



i i i i I i i 



+4 — M M — i 



1 I ) 



15 



20 



25 



30 



35 

ALPHA 



to 
CDEGD 



45 



50 



60 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFEREf>CE OI^ENSICNS 




CENTER OF GRAVITY XO » FS I07S.7 IN. 


WING AREA SW » 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN 9H - 78.056 


FT. 


MCTCNT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY LENGTH LB « 1290.7 


IN. 











ALPHA 


(OEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40 . 000 


45.000 


50.000 


CCLSB <DEG> 


F 


G 


H 


I 


J 


K 


L 


M 






SPEED 


BRAKE LIFT 


FORCE INCREMENT 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00050 


-0.00040 


-0.00030 


-0.00020 


-0.00010 


0.0 


0.0 


0.0 


H5.000 


-0.00115 


-0.00110 


-0.00060 


-0.00030 


-0.00011 


0.0 


0.0 


0.0 


55.000 


-0. 00175 


-0.00160 


-0.00100 


-0.00030 


-0.00009 


0.0 


0.0 


0.0 


70.000 


-0.00341 


-0.00270 


-0.00150 


-0.00100 


-0.00050 


0.0 


0.0 


0.0 


87.200 


-0.00730 


-0.00570 


-0.00410 


-0.00300 


-0.00150 


0.0 


0.0 


0.0 



EN3INEErJDC^P> 

DATE__3.^iXr.E> 



FIGURE 4.1.2.1-85 

ETECT Cr SPEEDBRAKE 



4.1.2.1-88 



FB72-SK-CCC0 1M 



11* 



Rockwell International 

Spaca Divwon 



1_ 



!*/ CH NUMBER 

7T1 



DEL SB CDEGD 

_50 100 







CONFIGURATION . 




BASELIhE CR9ITER VEHICLE 


REFERENCE DlrOSICNS 




CENTER OF GRAVITY XD - FS 1075.7 [N. 


WING AREA SW - 2690.00 


SQ.FT. 


OR YO « a. 0.0 IN. 


WING SPAN SW - 78.056 


FT. 


MCTENT REFERDrE 20 - M. T75.0 IN. 


M.AC. CW - 39.560 


FT. 




BCC LENGTH LB - 1290. T 


IN. 











ALPHA 


(CC6) 








-10.000 


-5.000 


0.0 


5.000 


1C.000 


15.000 


20.000 


25.00C 


CELSB IC£G> 


A 


8 


C 


D 


r 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCRE) 


f-ENT 






0.0 


0.0 


0.00157 


0.00210 


0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


. 00060 


O.OCOSO 


. 00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


CO 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00050 


-0.00051 


-0.00050 


-0.00045 


-0.C0040 


-0.00035 


-0 . 00030 


-0.00020 


45.000 


-0.00150 


-0.00155 


-0.00150 


-0.00130 


-0.C0110 


-0.00090 


-0.00070 


-0 . 00040 


55.000 


-0.00240 


-0 . 00247 


-0.00240 


-0.00210 


-0.CC180 


-0.00150 


-0.00120 


-0.00060 


70.000 


-0.00420 


-0.00436 


■ -0.00420 


-0.00355 


-0.30290 


-0.00235 


-0.00180 


-0.00110 


87.200 


-0 . 00830 


-0.00856 


-0 . 0C830 


-0 . 0074H 


-0 . 00620 


-0.00455 


-0.0C290 


-0.00940 



ENSINEER^^^ 

oate 3 --ivrriB- 



FIGURE 4.1.2.1-86 

EFFECT OF SPEEDBRA £ 



4.1.2.1-8C 



SD72-SH-CCeo JM 



1> 



Rockwell International 

Spac* Division 



r 



MACH NUMBER 



8.000 



.02 



OELSB CDEG] 

50 100 



02 

—J 



-.02 



-.04 



.06 



-.06 



i i i i I r~i i r~i i r~i r~i i i i 



j-.i ..1.-1- 



^^ jUii^jtja^^^jj .T yg ^T ^ mui h.h ia m- 



1 L..J- 



i. i 



_L 



1 IT 



I. I.L 



T~r 



! ' 1 



1^1 



-I.. 1 1 I 



I I I I 



"I I I I 



* — m — n- 



15 



20 



30 35 40 

ALPHA CDEGD 



45 



50 

a 



50 



CONFIGURATION 




BASELINE ORSITER VEHICLE 


REFERENCE DlrENSIONS 




CiNTER OF GRAVITY XO - FS 1075.7 IN. 


WING AREA S-f - 2690.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


U1NG SPAN BU • 78.056 


FT. 


1-CrENT REFERENCE ZO - UL 375.0 IN. 


M.A.C. CW • 33.560 


FT. 




BODY LENGTH LB - 1290.3" 


IN. 











ALPHA 


<C€G) 








15.000 


20.000 


25.000 


30.000 


15.000 


40.000 


45.000 


5C.000 


OELS3 (DEGi 


F 


G 


H 


I 


J 


K 


L 


M 


SPEEC 


GRAKE LIFT 


FCRC£ INCRE 


l-ENT 






0.0 


0.0 


0.0 


0.0 


0.0 


CO 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000. 


-0.00035 


-0.00030 


-0 . 00020 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0.00090 


-0.00070 


-0.00040 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00150 


-0.00120 


-0.00060 


-0.00020 


-0 . 00006 


0.0 


0.0 


o.c 


70 . 000 


-0 . 00235 


-0.001SO 


-0.00110 


-0.00040 


-0.00012 


0.0 


0.0 


0.0 


97.200 


-0 . 00455 


-0 . 00290 


-0.00240 


-0.00190 


-0 . 00095 


0.0 


0.0 


0.0 



ENGINEER ££D 

DATE,„3fI3i:!l£> 



FIGURE 4.1.2.1-87 

EFFECT CF SPEEDBR^ <E 



■4.1.2.1-90 



SD7 2-SH-CGC I M 



* 



Rockwell International 

SpacaDtaHon 



w ./ CH NUMBER 



10.000 



OELSB CDEG) 

50 100 

| I I I I | I I ■ ' 






-.ca 



-.04 




-.06 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE OltOGIONS 




CENTER OF GRAVITY XO - FS" 1076.7 IN. 


WING AREA SW « 2690.00 


so.rr. 


OR YO - BL 0.0 IN. 


WING SPAN BW • 78.056 


FT. 


MTOfT REFERENCE ZO ■ WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BCOY _ENGTW 1.8 - 1290.3 


IN. 



r 








ALPHA 


(DEG) 










-10.000 


-u.OOO 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


CCSB :C£G) 


A 


B 


c 


D 


E 


F 


G 


H 




SPEED 


BRAKE LIFT 


FORCE INCREI 


*€NT 






0.0 


0.0 


0.00157 


0.00210 


0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.00060 


. 00080 


0.00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00050 


-0.00051 


-0.00050 


-0.00045 


-0.00040 


-0.00035 


-0.00030 


-0.00020 


45.000 


-0.00150 


-0.00155 


-0.00150 


-0.00130 


-0.00110 


-0.00090 


-0.00070 


-0.00040 


55.000 


-0.00240 


-0.00247 


-0.00240 


-0.00210 


-0.00180 


-0.00150 


-0.00120 


-0.00050 


70.000 


-0.00420 


-0.00436 


-0.00420 


-0.00355 


-0.00290 


-0.00235 


-0.00180 


-0.00110 


87.200 


-0.00930 


-0.00856 


-0 . 00830 


-0.00744 


-0.00620 


-0.00455 


-0.00290 


-0.002*0 



ENGINEER 23SCt? 

QATE._isH3£H!!S> 



FIGURE 4. 1.2.1- 88 

EF-ECT OF SPEEDBRArE 



4.1.2.1-91 



SD 



72-SK-CCCC IM 



'Jt 



Rockwell International 

Spac*DMHOfl 



MACH NUMBER 



10.000 



DEL SB CDEGD 

O 50 100 



.OS 



I I I I 



K 



.0 f— 



■ — r f~ r< ^i tS ^^^^ ^ f U i^^^*^^V^i^ l _^_>MiJJi^ia - i ^ 



CO 
to 
_l 

o 
o 



.02 



-.04 



-.06 



.08 



. 1 II 



I I i l 



I I 1 l 



I I I I I I I I I 



1 I I 



X 



l i i | I l I I I I 



J (p«iUft . iKL Hi IK ^<-M ■ M 



15 



20 



30 



35 

ALPHA 



I ! 1 I I I I 
40 

CDEG3 



1 L. 



45 



50 



MM 



**— » M- 



M M 



60 



car i (juration 




BASELINE 0R8ITER VEHICLE 


REFERENCE DI^£^SI0NS 




.ENTER OF GRAVITY XO « FS 1076.7 IN. 


MING AREA SU - 2590.00 


SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BU - 78.056 


FT. 


MCt-ENT REFERENCE Z0 - W_ 375.0 IN. 


M.A.C. CW - 39.550 


FT. 


. 


BODY LENGTH LB • 1290. J 


IN. 











ALPHA 


(CEG) 








15.000 


20.000 


25.000 


30.000 


35.000 


40.000 


45.000 


50.000 


CELSB (CEG) 


F 


G 


H 


I 


J 


K 


L 


M 






SPEED 


BRAKE LIFT 


FORCE INCTOENT 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00035 


-0.00030 


-0.00020 


0.0 


0.0 


0.0 


0.0 


0.0 


45.000 


-0.00090 


-0 . 00070 


-0.00040 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00150 


-0.00120 


-0.00060 


-0 . 00020 


-0.00006 


0.0 


0.0 


0.0 


70.000 


-C . 00235 


-0.00180 


-0.00110 


-0.0D040 


-0.00012 


0.0 


0.0 


0.0 


87.200 


-0.00455 


-0 . 00290 


-0.00240 


-0.00190 


-0.00095 


0.0 


0.0 


0.0 



ENGINEER ± 

DATE_.lr.L"kf 



FIGURE 4.1.2.1-89 

EFFECT OF SPEEDERAKE 



4.1.2.1-92 



«- i i *- — o r; 



OCCC IM 



'1* 



Rockwell International 

SpacaDtviaon 



MACH NUMBER 



15.000 



DELSB CDEGD 

50 100 



: P"-| i ; j i i i i I , i i i I i i i i 



1 



.02 



en 




-.06 



-.08 



J_L 



I'll 



1 I 1 I 



J, -I... 



J_ 



n — mm" 



_L 



M M I M I I 



jg£^^jjw v»JJ^jgjj ht* * t = *a & ^. 



I I I I 



I ,1 i-L 



-10 



10 

ALPHA 



15 

CDEG) 



20 



30 



CONFIGURATION 




BASELINE ORBITER VEHICLE 


REFERENCE DlfENSICtS 




CENTER OF GRAVITY XO - FS 1076.7 IN. 


klNG AREA SW - 2590.00 


SQ.FT. 


OR YO - BL 0.0 IN. 


WING SPAN BU - 78.056 


FT. 


M>£NT REFERENCE 20 « WL 375.0 IN. 


M.A.C. CW - 39.560 


FT. 




BODY LENGTH LB - 1290.3 


IN. 











ALPHA 


(0EG1 








I 


-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


i 


A 


B 


C 





E 


F - 


G 


H 


,C€-SS iC£G: 






SPEED 


BRAKE LIFT 


FORCE INCRE1 


KENT 






0.0 


0.0 


0.00157 


0.00210 


0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.00060 


0.00080 


0.C0040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.C 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00050 


-0.00051 


-0.00C50 


-O.C0045 


-0.0OO40 


-0.00035 


-0.00030 


-0.00020 


45.000 


-0.00150 


-0.00155 


-0.00150 


-0.00130 


-0.00110 


-O.OOOSO 


-0.00070 


-0.00040 


55.000 


-0.00240 


-0.00247 


-0.00240 


-0.00210 


-0.00180 


-0.00150 


-0.00120 


-0.00060 


70.000 


-0 . 00420 


-0 . 00438 


-0 . 00420 


-0.C0355 


-0.00290 


-0.00235 


-0.00180 


-0.00110 


87.200 


-0.00830 


-0.OC856 


-0.C0830 


-0.C0744 


-0.00520 


-0.00455 


-0.00290 


-0.00240 



ENGINEER -U^D 
DATE ££IS}l?5' 



FIGURE 4.1.2.1-90 

EFFECT OF SPEEOBRAKE 



4.1.2.1-93 



SD 



- r-. r 

( £- - w 



H-CCCC IM 



'i* 



Rockwell International 

Spae* Dtvwon 



MACH NUMBER 



15.000 



.02 



r 



1 1 1 1 1 1 






-.02 



.04 



-.06 



r^f^^7r ^^* L ^J.^ r _l 1 _'_L4. ''' f 'h i t" " n v t kui ;l.'i hh 



.081 -L I..I.L. 
15 20 



I I I I 



OELSB CDEGD 

50 100 

I I I I I I 



Ti 



I I i I 



XJ_ 



J_ 



I, ! I 



I I I I 



30 35 HO 

ALPHA CD'.GD 



l l l 



T 



i i i I 



I I i i 



H— « H— 



■i-l-i, I 



45 



50 



COFIGURATION 



BASELIhC CRB1TER VEHICLE 
CENTER OF GRAVITY XO - FS 1075.7 IN. 
OR YD - BL " 0.0 IN. 

MCfENT REFERENCE ZO - WL 375.0 IN. 



REFERENCE DlrtNSIONS 
WING ARE.. SW » 2690.00 SQ.FT. 
WING SPA/. BW - 78.056 FT. 
M.A.C. CW - 39.560 FT. 

. 9COV LENCTH LB » 1290.3 IN. 



OELSB (OEG) 



0.0 
15.000 
25.000 
35.000 
45.000 
55.000 
70.000 
87.200 



15.000 

F 



20.000 
G 



ALPHA (CEGl 



25.000 
H 



30.000 



35.000 
J 



to. 000 
K 



0.0 

0.0 

0.0 
-0.00035 
-0.00090 
-0.00150 
-0.00235 
-0.00455 



0.0 

0.0 

0.0 
-0.00030 
-0.00070 
-0.00120 
-0.00160 
-0.00290 



SPEEDBRAKE LIFT FORCE INCREt-gNT 



45.000 

L 



0.0 

0.0 

0.0 
-0.00020 
-0.00040 
-0 . 00060 
-0.00110 
-0 .00240 



0.0 

0.0 

0.0 

0.0 

0.0 
-0.00020 
-0.00040 
-0.00190 



0.0 

0.0 

0.0 

0.0 

0.0 
-0 . 00006 
-0.00012 
-0 00095 



0.0 
0.0 
0.0 

0.0 
0.0 
0.0 
0.0 

0.0 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
CO 
0.0 



60 



50.000 
M 



0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 
0.0 



ENGIhCER -XjxI^* 

date ..il;:5Cw3 



FIGURE 4.1.2.1-91 

. EFFECT OP SPEEDBRAKE 



4.1.2.1-94 



t 



L 72 -SI-'- CCCC IM 



€* 



Rockwell International 

Spac*Dhnaton 



MACH NUMBER 



20.000 



OELSB (DEG5 

50 100 

, I i i I I i I I 



o 




-.06 



CCNF I CURAT ION 




BASELINE CR9ITER VEHICLE 


REFERENCE DIMENSIONS 




CS.MTE3 OF GRAVITY XO - FS 1075.7 IN. 


WING AREA SW - 2690.00 


SQ.FT. 


CR YO - BL 0.0 IN. 


WING SPAN BU - 78.055 


FT. 


MO*tNI Hfc>tHLNCL ZO - UL 3V5. IN. 


M.A.f CW ■ 39.560 


FT. 




S0OY LENGTH LB » 1290.3 


IN. 











ALPHA 


^EGl 








-10.000 


-5.000 


0.0 


5.000 


10.000 


15.000 


20.000 


25.000 


OELSB (DEC) 


A 


8 


C 


D 


E 


F 


G 


H 






SPEED 


BRAKE LIFT 


FORCE INCREMENT 




0.0 


0.0 


0.00157 


0.00210 


0.00105 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.00060 


0.00080 


0.00040 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00050 


-0.00051 


-0.00050 


-0.00045 


-0.00040 


-0.00035 


-0.00030 


-0.00020 


45.000 


-0.00150 


-0.00155 


-0.00150 


-0.00130 


-0.001 10 


-0.00090 


-0.00070 


-0 . 00040 


55.000 


-0 . 00240 


-0. 0024 7 


-0.00240 


-0.00210 


-0.00180 


-0.00150 


-0.00120 


-o.oocso 


70.000 


-0 . 00480 


-0.00436 


-0 . 00420 


-0.00355 


-0.00290 


-0.00235 


-0.001B0 


-0.00110 


87.200 


-0 . 00830 


-0 . 00856 


-0 0083C 


-0 . 00744 


-0.00620 


-0.00455 


-0.00290 


-0.00240 



ENGINEER Sky 
DATE *-!%-££> 



FIGURE 4.1.2.1-92 

EFFECT OF SPEEDBRAr.; 



4.1.2.1-95 



SD72-SH-OCCO IM 



* 



Rockwell International 

Spac* DhMion 



MACH NUMBER 



.02 



|: — P - P--B. 



_J 



-.02 



-.OH 



.-.06 



-.08 



i • i i iiit n 



■ ■ i 



l, .i,.i. „ i. 



20.000 

i i i i i i 



DELSB CDEGD 

50 100 

i i r 1 



i ^ l^ ^Juiuulag^yW\j*^^4^\lto^WM*&- < }X\Jl. HJ 4 nt 



-L_L 



_L 



I I 



I I I I 



I I 



MM 



i'i: 



15 



20 



30 35 "0 

ALPHA CDEGD 



H5 



50 

4 



CONFIGURATION 




BASELINE 0R8ITER VEHICLE 


REFERENCT DI^€^SICNS 




CENTER OF GRAVITY XO « FS 1075.7 IN. 


WING AREA SU - 26S0.00 


SQ.FT. 


OR Y0 • BL 0.0 IN. 


WING SPAN BW - 78.055 


FT. 


M>ENT REFERENCE 20 - WL 375.0 IN. 


M.A.C. CW » 39.560 


FT. 




BCOY LENGTH LB » 1290.3 


IN. 



DATE..ar?,X-l5 



FIGURE 4.1.2.1-93 

EFFECT CF SPEEDBRAKE 



I i I I 
MM 



+4— M M- 



1 ' ! ' 



55 



60 











ALPHA 


tXG) 








15. CC0 


20.00C 


25.000 


30.000 


35.000 


HO. 000 


H5.000 


50.000 


0ELSB (C£G) 


F 


G 


H 


1 


J 


K 


L 


M 






SPEEE 


6RAKE LIFT 


FORCE INCRE 


f-ENT 






0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


15.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


25.000 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


35.000 


-0.00035 


-0 . 00030 


-0.00020 


0.0 


0.0 


0.0 


0.0 


0.0 


H5.000 


-0 . 00090 


-0 . 00070 


-0.00040 


0.0 


0.0 


0.0 


0.0 


0.0 


55.000 


-0.00150 


-0.00120 


-0.00C60 


-0.00020 


-0 . 30006 


0.0 


0.0 


0.0 


70.000 


-0 . 00235 


-0.00180 


-0.00110 


-0.00OH0 


-0.30012 


0.0 


0.0 


0.0 


87.200 


-0. 00*4=5 


-0.00290 


-G.0C2H0 


-0.00190 


-0 . 30095 


0.0 


0.0 


0.0 



L. 1.2.. .-96 






■H-CC60 1M 



'1* 



Rockwell International 

Space Division 



cotioliution 




hi i* owrm vomclc 


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100.000 

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300. 90C [ 

•40.900 '< 
MO.ioe ' 



l.i 

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0. 
0. 
0. 



1 .90000 

g.am 

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9. 




PICO ! 



i.oacoo 

o.sbim 
o.arNo 

9.9*323 

a face 



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3. 90380 

9.BB100 

3.90200 



i.acooo 

C-9BT! 
3.3003 
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9. gits' 

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0. 99107 

9.9*1] 

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9CT7 



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a. BOZO 
O.BBM 

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i.sooT 


t.ooo 


1.5O0 


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3.900 


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10.000 


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• 




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0.9 


1.900001 


1.90000 


1 .90000 


i.ooooo 


i.SOtJ) 


,.33030 


1.90000 


1 .30000 


1.90000 


100.900 


o.afTSl 


0.9BWTI 


0.9BEI 


0.BBH 


o.aa>oc 


9.90*1.3 


0-SBK7 


° ■■■'■! 


0.OOB3 


290. COO 


O.S*W» 


a.SBtn 


9.9B707 


o.anu 


9.9BB0 


9.*B*S7 


B — M 


a.wnT 


o.m*? 


BO. 000 


o.aiiTfl' 


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0.9BBW 


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0.9B*ro 


a.ajT-i 


O.OJTO 


U.Wl* 


«•"■■ 


•00.000 


I.MDI 


0.9KIJ 


d.»l] 


0.9BBC 


0.9SB00 


9. mm 


O.flf07 


a.arrs 


9.97S 


SSO.SW. 


9.9B8I-I 


9.9B0I7 




5.9SWJC 


e asm 


: «r 


a. sacs 


a.&esr 


'J.T&3B' 



._.,__, o^: ^- FIGURE L.I. 2. 1-91 „ , 

oSzS^Sl FLEX/RIGID NORMAL 3RC: COR LIFTD SLOPE WITH ALPHA 



.1.2.1-97 



SD72-SH-OCTO 1M 



& 



Rockwell International 

Space Divaioo 



CCW10UUTION 
IMB.I>C CW11T* XXICLC VTHXI aix>«ia« 

ohw or oawirr jo - n iffTi.7 ih. 4twj ajca S4 • sso.so a.rr. 
o» to • a. o.o m. -ixj v* noa rr. 

■OWT ^T^D^ n • i*. 175.0 IN. H.A.C. :> • 30 MO fT. 




*ca*« «ti 








"• aro. 


.:r* l 1 ■ t, t**>C5 








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i .090001 


1.30000 


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t.ccooo 


i.ieeeo 


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100. ao 


3. ease 


o.ooijj 


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s.noa ' 


0.993V I 


0.96087 


0.30090 


9.993B0 


0.99900 


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0.9MX, 


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3.92000 


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9.993770 


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ENG 

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-*£r 



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FIGURE u. 1.2. 1-95 
P^;X!9LE/RIGID ELEVQN LIF" EFFECTIVENESS 



4.1.2.1-98 



SD 72 



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SD72-SH-CCC0 I M 



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Rockwell International 

SpacsOivmon 



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wn.aoo 


8.00171 


0. oocn 


0. 900 11 


0. 00006 


0.00003 


0.0 


0.0 


0.0 


0.0 


^00.000 


3.00*13 


•Jfiffl 


_..ll="'? 


3 -'WOT 


. o.saaj 


0.0 


0.0 


0.0 


0.0 



PCIWCT <&&& ■ FIGURE i. 1.2.1-97 

date Y-A-7J . FLEXIBLE LIFT INCREMENT AT ZERO ANGLE CF ATTACK 



t. 1.2. 1-100 



SD72~SH-OCCO i 



M 



'1* 



Rockwell International 

SpactDfcwon 



L 



ALPHA CDEGD 

20 40 

I I I I I 



o 
a 




-.005 



40 60 80 

TrlETA CDEGD 



COvFIGLKATICN 



BASELINE CRBITER VEHICLE 

CENTER OF GRAVITY XO - FS 1075.7 IN 

OR - YO « BL 0.0 IN 

MOT-EMT REFERENCE ZO • U- 375.0 IN. 



REFERENCE DIfCNSIONS 
UIN3 AREA SW » 2690.00 SQ.FT. 
WING SPAN BW « 78.055 FT. 
M.A.C. CW » 39.550 FT. 

BOOY LENGTH L8 - 1390.3 IN. ._ 



ALPHA <C€G) 



-10.000 
-5.000 

0.0 

5.000 
10.000 
15.000 
20.000 
£5.000 



THETA (PEG) 



0.0 
A 



1 .OCu 
B 



4 . aoo 
c 



10.000 
D 



23.000 
E 



53.000 

F 



83.000 

G 



96. oca 

H 



LANDING GEAR LIFT INCREMENT 



0.0 


i . 00090 


0.0 


L . 0C058 


0.0 


C .00031 


0.0 


0.00010 


0.0 


-0.00007 


0.0 


-0.00024 


0.0 


-0.00039 


0.0 


-0.00044 



0.0030! 

0.00194 

0.00102 

0.00034 

-0.00022 

-0.00079 

-0.00129 

-0.00146 



0.00489 

0.00315 

0.00156 

0.00055 

-0.0003S 

-0.00129 

-0.00509 

-0.00238 



0.00791 

0.00509 

0.00259 

0.00088 

-0.00058 

-0.00209 

-0 . 00338 

-0.00384 



0.01205 

0.00776 

0.00410 

0.00134 

-0.00089 

-0.00318 

-0.00515 

-0 . 00585 



0.01544 

0.00994 

0.00525 

0.00172 

-0.00114 

-0.00407 

-0.00660 

-0 . 00750 



0.01732 

0.01115 

0.00539 

0.00193 

-0.00128 

-0.00457 

-0.00740 

-0 . 0094 '. 




FIGURE 4.1.2.1-98 

L AND ! NG GEAR LIFT COEFFICIENT INCREMENT 



.4.1.2.1-101 



SD7.:-SK~CCCO 1M 



0& 



Rockwell International 
SpacaOhwon 




Landing G»ar Down 



fc 



ACi =C, 

'"* u 3tOUNO L O»OUN0 
tWtCT (MSCT 



UNO* •■ «M 

ST*L*M 



CONFIOUf-ATION 

UUIHC JlliTU IfllCU 
until a» <M««r» ,i,i>i imjl 
%•» LM 
!.«■■» J7VJI 
UFllCICt SIMCUiUS 

k.* 7L9U h 
w« 3LSM. 



Aq.. 



at 




0.2 



O.* 




0-6 0.8 t.O 

HEIGHT/SPAN 



f. h/b 

X. 1906.34 

z« 2«a.7- 



1.2 



l.H 



l.S 



^ 







AngU of Attack, a — 


D»gr*«s 






a-h.ooo 


I 0.0 


e h.ooo | c 


8.000 


t 12.000 


t 16.000 


a 2a.ooo 




l»cr«* 


iwntal Lift 


Foret 


Coefficient ,AClo«N8.F»*rr 


0.029 


0.32000 


-o. mooo 


. 08000 




0. 12000 


0.18000 


i.. 27000 


. 35000 


0.3SO ' 


-0.255HO 


-0.11810 


0.06970 




0.09000 


0.1IS80 


. 08890 


0. 11H50 


0.10O 


-0.18800 


-0 . 07600 


0.03030 




. 06600 


0.08390 


0.0B260 


. 08750 


0.2SO 


-0 . 09020 


-0 . 03880 


. 00830 




0.03810 


0.05190 


0.08380 


. 073b0 


0.300 


-0.0<«950 


-0.02960 


0.0 




0.02800 


. 0399O 


. 05550 


0.07E30 


0.300 


-0.02930 


-0.01720 


0.0 




0.01650 


0.02730 


0.02980 


O.OMOO 


1.000 


-0.010CO 


-O.OOSOO 


0.0 




0.00200 


0. 00*00 


0.00600 


0.00800 


i.hm 


0.0 


0.0 


0.0 




0.0 


0.0 


0.0 


0.0 



INCINU* 

OAT! ta-^-yy 

(EV1SED: 



Figure 4.1.2.1-99 

GROUND EFFECT 



4.1.2.1-102 



SD72-SF-GCeo IM 



€> 



Rockwell International 
Somc»Ctvmar\ 



'. v>_.- 




Lancing G*ar Down 






OIQUNO L G»OUNO 




COMNOUtATlON 
i»«u« iiiirti tnicu 

anni a* wamit it,"* 1171 Jt 

am (% •» LM 

■cMtHT niwin <(.*«4 JTUt 

IfFCKlCI ttHOSIMf 

uu wilHJttfc' 

.** ... JliH- 

•ear i»«n< w» • 19UM - 



ACt c 




0.2 



0.* 



0.6 0.3 1.0 

HEIGHT/SPAN 



1.3 



I.H 



1.5 




f, h/b 

X.150«.14 



MllO-HT^ 
•VAN 

h/b 


AngU of Artncic, Ct — D«gr««i 


A -H.aoo 


1 0.0 jc H.000 


3.000 


( 12.000 


f 18.000 


c 20.000 




Incremental Lift Foret 


Co«ffiei« 


»"' .A^la 


« N .tE"f^ 


0.029 


-0^29000 


-0.18500 


-0.09000 


-0.07 00 


0.01000 


0.25000 


0.30000 


O.OSfi ' 


-0.23590 


-0.16380 


-0 . 09500 


-o.07<iia 


-0.01000 


0. 1*210 


0. 200*0 


0.100 


-0.16930 


-0.11730 


-0 . 39880 


-0.0T 30 


-0.02*60 


0.0*0*0 


0.-09660 


0.200 


-0.09270 


-0.053*0 


-oaooio 


0.02 30 


. 05530 


0.07310 


0.08200 


0.300 


-0.059*0 


-0.022*0 


01070 


0.0c 30 


o.o*060 


0.0**30 


0.053*0 


0.500 


•0.03030 


-0.00620 


. 00530 


0.01-10 


. 025 1 


0.02660 


0.03200 


1.000 


-0.00700 


-0.00500 


0.0 


0.00. 00 


o.oo»oo 


0.00600 


0.00800 


1.500 


a.o 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



oati j2; 



JL 



1Z2Z. 



Figure t.1.2.3 -100 

GROUND EFECT 




t.l.2.L-103 



SD72-SH-OCGO 1M 



'i* 



Rockwell intemationaJ 

SoacmCtvmon 




Landing G*ar Down 



AC l-<5.OUN0 =C l- 
!M€CT 



giouno" t- ntt 
vrKT 



STMAM 




S.= -20.000 c 



5„ = -11.7' 



CONFIGURATION 

IMUIIE 9II4TT1 tfllRI 
cihtu or oxmtt ^iiiiTUl 

icrcicxei jiatuieu 

•»■ w» 7I.8S* ■> 

~« <,■ n.sH« 

•ear i»«» i* • I3UM - 



S » S .AA. 



8\ 



AClo, 



.0 



-.* 





i i : 


i i i 


i 1 i 


1 i — 


i i ' ; 


i i i 


- 


-\\ 














_ 


-g Tv^V^. 














- 


- ^^v^J^ 










i- 




- 


3*-y , 


t___p— — ■ 














i i i 


i r i 


,1 ,1 ! ,. 


L ,. 1 


i i i 


i > I 


i i i 



0.2 O.H 0.6 0.8 

HEIGHT/SPAN 



i.o 



1.2 



I.* 



1.6 




INGINEfr 



AL 



height/ 

SZTAM 

h/b 




Angle of Attack, a — Degrees 






A -H.000 


1 0.0 


c h.ooo | o s.ooo 


1 12.000 \f 18.000 


G 20.000 


Incremental Lift Fore* Coefficient , A^Lowo . Me<r 


0.025 


-0. HOOOO 


-0.28000 


-0.20000 


•'o.o" 


0.10000 


0. 2*000 


0.30000 


0.090 ' 


-0.29000 


-0.22000 


-0. 15000 


-0.003>-0 


. 08070 


0.18380 


0.23000 


0.100 


-0.21000 


-0.1 5320 


-0.09**0 


-0.0U20 


0.0*600 


0.10170 


0. 1*910 


0.200 


-0.12500 


-0.08060 


-0.033*0 


-0.01390 


0.00910 


0.0*560 


. 07590 


0.3O0 


-0.08000 


-0.0*600 


-0.02-00 


-0.00730 


0.00100 


0.02*50 


0.0*000 


o.sao 


-0.0*000 


-0.02500 


-0.01500 


-0.00110 


0.0 


0.01290 


0.02610 


1.000 


•0.01000 


-0.00500 


-0. 00*00 


-0.002H0 


0.0 


0.00200 


0.00500 


i.soa 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



((VISED 



Figure 4.1.2.1-101 

GROUND EFFHCT 



4.1.2. 1-1C4 



SD72-SH-C CCC IM 



I! 



€> 



Rockwdl IntemattonaJ 

SoacaOtMaon 




Landing Omar Down 



" 1-ohouno" 1-shouno "^ '«*! 

IHJCT 8FMCT 5T*lAM 



10 C| -.,f| 




5 = -15.000 

9 



5„s-:i.7« 



CONHOg RATION 

MKlilC Mlini fCMCU 

CIMrn Of OUOTTT |I,II| l|7tJt 

i»«* 17VM 

unmet hikunu 
imm »»« tun » 

•oar ji m i l, • 12MJM « 



S\ 



V5 

5 S ,= A11 



4 C U« 




0.2 O.t 0.6 0.8 1.0 

HEIGHT/SPAN 



1.2 



l.H 



1.6 




•Van 

h/b 




Angl* of Att 


ock, cc -* Degrees 






A-H.000 


, 0.0 


c *.ooo 


3 8.000 


( 12.000 


t 16.000 


G 20.000 




Incremental Li 


ft Force 


Coefficient , &Cl 


RNO^'K? 


0. 029 


-o.hoooo 


" -6727000 


-a. iiooo 


0.0 


0.19000 


0.26000 


0.30500 


0.050 ' 


-0.29910 


-0.18090 


-0.11010 


0.3 


0.12070 


0.20270 


0.23V 80 


0.100 


-3.20950 


-0. 12330 


-0 . 06700 


0. 


0.067*0 


0.12590 


0.1>*680 


0.200 


-0.11600 


-0.06520 


-0.03070 


0.3 


0.033HO 


0.06910 


0.08150 


0.380 


-0.071HC 


-0.0H130 


-0.01790 


0. ) 


0.02250 


0.05120 


. 05870 


0.900 


-0.03660 


-0.01900 


-0.00550 





0.01210 


0.02830 


. 03280 


1.0 00 


-0.00800 


-0.00200 


-0.00100 


0.J 


0.00200 


0.00<*QO 


. 00600 


1.900 


0.0 


0.0 


0.0 


o.: 


0.0 


0.0 


0.0 



INGINUR' 

«fV!S£0: 



Figure 4.1.2. .-102 

GROUND EFFECT 



4.1.2.1-105 



SD72-SH-OCeO IM 



€* 



Rockwell International 

SpaeaChwon 




Landing G«ar Down 



fc 



HMCT eMICT JTllAM 




«• = 



-10.000' 



5 1P = -L1.7« 



CONFIOUKAttON 

UHLIIf 9II1TT1 fCWCU 

ciwru of o»*».rr j !,•»« ifTUl 

n oiilirt UWKI (U"X» 371M 
lEFEIEXCt giMIUIMI 

««•* w*2IH.IMi.- 



5 U =A11 



AC 



-<st 



.0 



-.2 



i : . 


' I ' i ■T" _ 


i i i 


l 1 1 


1 , ! 


i 1 T _ 


i 1 1 


- 


: ^1 


r~ § 












- 



















V 

.1,.. ! [ 


i i i 


t ' r 


1 ! I 


1 ! ! 


! r i 




li l 



0.2 



0.* 



0.5 0.8 

HEIGHT/SPAN 



1.0 



1.2 



I.* 



l.S 




f„ h/b 

I. 1S0«.«4 

Z, 212.71 



JNG1NM* :_Z 

OAT! ^-/^y- 77 



HUGH \S 


Angla of Attack, Ct — 


3«gr»«i 






a-h.OOO [| 0.0 


e t.ooo 


8.000 


< lz.ooo 


f IS. 000 


,-20.000 


Incrtmantai Li 


ft Fore* 


Coafficianf t ACLc»No.yKT 


o.aes 


-0.33000 


-0.22000 


-0.10000 


~u.*<n5oo 


0. 18000 


u.eSCOO 


0.320 (CO 


0.0M ' 
0.20Q 


-0.28500 


-0.18780 


-0.07180 


0. 05800 


0.1*380 


0.23290 


0. 25590 


-0.22030 


-0.13080 


-0. 0*780 


. 1.03000 


. 09280 


0.15150 


. 1 7360 


0.200 


-0.11680 


-0 . 06380 


-0.02*30 


0.31000 


0. 0*120 


0.07060 


0.08SOO 


0.3S0 


-0.07030 


-0.03630 


-0.016*0 


0.01090 


0.02000 


0.0*380 


0.05*50 


0.300 


-0.03220 


-0.01530 


-0.00**0 


. 00**0 


0.OICOO 


0.02550 


0. 03310 


1.000 


-0 . 00700 


-0.00200 


0.0 


0.0 


0.00100 


0.00200 


0.00300 


1.500 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



Figora 2, .1.2 .1-1C "' 

GROUND EFFECT 



4.1.2.1-106 



SD72-SH-CC6 



C 1M 



. I 



'1* 



Rockwell irtemattcnai 
ScacaOtaoian 




Landing G«or Down 



A^tatouNlT '■GtOUNO 



•3IOUN0 
8MICT 



l*MCT 



ST*tAM 1 




5,= _-5.000° 



5„ = -11.7" 






CQH910U*ATIQM 
IMdllf oiutu icucu 

aunt o« UMif ri,*ill7tJI 

a* { % « h LW 

iwiiit uw— 3 <l»'«* J7UI 

icrcuict nvfuisu 

wu w« IIMJU h' 

ma k.> 7t.nt fc 

»*c v.- UJH- 

«o»» isaira l, • tSSUM - 



5 S1 =111 



*<*« 



-.2 




0.2 



0. 4 0.6 0.8 1.0 

HEIGHT/SPAN 



1.2 



1.4 



1.6 




>.r h/b 

x. isos.a* 

Z„ 2S2.71 



r r 

h/b 


Ang!« of Anoek, a ~ Dagr««s 






A -*.000 [, 0.0 


c '.000 


S.000 


( 12.000 


• 18.000 


20.000 


IrKromamal Lift Foret Ca«ffici« 


int , AC(.o»no •«*?€? 


0.025 


-C. 32000 


"-0. 18500 


-0 . 37000 


0. 10000 


0.22000 


0.32000 


0.-0000 


0.050 ' 


-0.23500 


-0.15240 


-0 . 05900 


0.07200 


0. 18380 


0.25480 


0.284*0 


0.100 


-0.16620 


-0.1 OH 30 


-0 . 32760 


O.0HH3O 


0.11720 


0.16900 


0.18370 


0.200 


-0.10580 


-0 . 05880 


-0 01070 


. 02090 


. 05260 


. 08590 


■ 09760 


0.300 


-0.07300 


-0 . 03760 


-0 . 00480 


0.01530 


0.02770 


0.05230 


0.36100 


0.300 


-0.03850 


-0.01610 


30170 


0.00330 


0.01530 


0.03130 


O.:3770 


1.000 


•O.Q0600 


0.0 


C 3 


0.00300 


. 00700 


a. an 00 


0.31700 


1.S00 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 


0.0 



iNGiNtir 

OaTI <•/' 

MVI3C0: 



£1- 



FIgur* 4.1.2.1-104 

GROUND EFFECT 




4.1.2.1-107 



SD72-SH-OCCC IM 



'i* 



Rockwell international 

ScacaQfcriaon 



Landing Goor Down 




!WICT H«CT ST«EA*> 




5,= 0.0 



5„ = -U.7* 



^CO»«r<IOU«ATlCN ^ 

imuic 9111TU taicii i 

175-11 






UfUUCt 8IM1S1US 

.ma w-:ih.»»«h' 

«< ,. • 1UM > 

KMT IMTK L, • I2MJM » 



5 U =J^. 



^Hh5« 




0.2 0. 1 * 0.5 0.8 1.0 

HEIGHT/SPAN 



1.2 



l.H 



1.6 




Ur h/ 3 
X. 180«.fl* 
I, ZtZ.Tl 



■ 

MKGHTX 

"A 


Anglo of Attoek.a ~ Dogr*o« 




A -H.000 


1 0.0 


c <*.000 


8.000 j | 12.000 


f 16.000 


(.20.000 




Incromontal Lift Foreo Coofficii 


»"' ,&Clo 


*NO ^F»?CT 


0.029 


-o. laooo 


" oioesoo 


" 0." 05000 


0.16500 


"3.25O00 


0.28500 


0.30000 


o.cao " 


-0.16500 


-0.07520 


0.03930 


0.13V90 


0.205M) 


0.250*0 


0.26350 


0.100 


-0.13920 


-0.055B0 


0.02*80 


. 095H0 


. 1 3690 


0.17580 


0. 191 10 


0.200 


-0 . 08950 


-0.03590 


0.01010 


0.0HOHO 


0.06390 


0.09060 


0.10230 


0.330 


-0.06060 


-0.02230 


0.00510 


. 02230 


. 0HH50 


0.06200 


0.069*0 


0.300 


-0.022HO 


-0.01080 


0.00350 


. 1 090 


. 02580 


0. 02900 


0.03*30 


1.0 00 


-0.00500 


-0 . 00200 


0.0 


0.0 


. 00200 


0.00*00 


0. 00800 


1 1.900 


0.0 


0.0 | 0.0 


0.0 | 0.0 


0.0 


0.0 



tNCIHt» - jf> 

MVIJJ3; 



Figure 4.1.2.1-105 

GROUND EFFECT 



t. 1.2.1-108 



SL"J2. SH-CCCO IM 



8 



Pcckweil SntsfiTitScnaJ 

SpacaCtaro 




landing G*ar Oown 

IWiCT !F»KT 5T3t*M 








cckhou&a7!om 
mum gisiru iohsu 



5.= 5.000' 



s„=-u.r 



et < %<m Lit 

imm *,■ 71.3M n 

ism i»«n ^ • l^-'i* - 



5„= All 



^<< 



ct 




0.2 



0.4 




0.6 0.3 1.0 
HEIGHT/SPAN 



llUfHtl F»i»i 

t.r h/b 

X,lS0«.i4 

Z, 212.71 



1.6 



HUGMT, 



•VAN 



0. 
0. 
9. 
0. 

0. 
0. 

1 

I 



029 

oso ' 
too 

200 
300 
300 
.900 
.500 



Ang)< of Attack, a — Dogrt«i 



A -*».ooo 



0. j e H.OOO 8. 000 i 12.000 \t is. ooo qM.aoo 
Incremental Lift Force Coefficient , ACi ggH0 ■t«« ct 



-0.17000 
-0.15000 
-0.11990 

-0.07V 30 
-0 . 0*650 
-0.01870 
-0.0CHC0 

0.3 



-0.08000 
-0.06530 

-o . OHoao 

-0 . 02620 
-0.01830 

-0.00710 
-0.00200 
3.0 



0.10500 
0.06710 
. 05990 
. 02290 
0.00330 
0.002H0 
0.0 
0.0 



3.13000 
0. 1*990 
0. 10160 
0. Oh 370 
. 1 980 
. i 070 
0.30200 
0.0 






2H000 





2S000 


-3 


31500 


3 


20970 





25360 


3 


27000 





14710 





13220 





19030 





06690 





09190' 





10 IOC 





03720 


3 


05503 





06070 





02260 


3 


03<»70 





S38H0 





30600 





01003 


3 


01230 


3 





3 


.3 


3 






(NGINIH>_ 

DAT! ■£ 

MVISJD- 



II 



K 



Four* 4.1.2.1-106 

GROUND EFFECT 



y 



4.1.2.1-109 



SD 72 -SH-OCCO 



M 



IjjJI 



Rockwd! irrtamafionai 

ScwcaDtvmon 




Landing G*or Oown 



•*MCT !FMC7 5T«t*M 




^ 



CONriOUIATlON 
iiuiik :inru uweu 

UMiM a» aumrr /«.<>« H7IJI 

o« | % » «. S.3* 

"•««' wmo li.'-»» 37SJI 

nnuntt iwtnim 

*«* wUM.Mli.- 

>»« »»» TLiH t, 

— < v. • J1.1M » 



5,= l"b. 000 



5„ = -U.7- 



fi M =Aii 



• 3r* 



AC t 



CI 




0.6 0.3 

HEIGHT/SPAN 



1.0 



1.2 



1.4 



1.6 



DAT! 



f.c K/b 
z. iso«.a<t 

Z« 282. 71 




•?-,**- 7 7 



3*v:iio- 



F'gor. 4.1.2.1-107 

GRCUf D EFFECT 



v^,- 




4.1.1.1-110 



J 



SD72-SH-CC 



C IM 



Rockwell International 
SpacaDivsion 




Landing Gear Down 



AC L 



= c, 

MMCT If 




— M^m^gHPMKJ^ I.1 M i n i 



AC L 



Gi 




It,' 'I ito-n | 



fi.slS.OOO' 



5„ = -il.7« 



uuuic juiTtj i,-AC;i 

CINfll 0» 0«A»ITT (I,<>»H7I./1 
•OalxT IfflMMCI 

■(FtA[4CE eiMEAStOAS 

&