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Full text of "NASA Technical Reports Server (NTRS) 20030016552: Analysis of X-33 Linear Aerospike Plume Induced Base-Heating Environment During Power-Pack Out"

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Analysis of X-33 Linear Aerospike Plume Induced 
Base-Heating Environment During Power-Pack Out 



Ten-See Wang 

Robert Williams and Alan Droege 
Mark D’agnostino and Young-Ching Lee 

Stan Douglas 


NASA - Marshall Space Flight Center 
April 4-5, 2001 



Acknowledgment 


Space Transportation Directorate 




John Suter of X-33 Program Office 


Space Transportation Directorate 


CFD Analysis of X33 Flex Seal Environments During PPO 



• Objective 

- Predict dual-engine base-heating at 57% PL at sea level 

- Predict dual-engine base-heating during PPO at 3 ascent abort trajectories 

• Approach 

- 3D turbulent chemically reacting computational fluid dynamic and heat 
transfer analysis (FDNS, GASRAD and GRASP) 

- Full-vehicle and slip stream effects with dual-engine, 40-thruster, and 
base-pillow bleeds 

- Benchmarks 

• 7.75% scaled model cold flow test 

• 2.25% scaled model hot flow test 

• Installed full-scale engine hot-fire test 


Space Transportation Directorate 


Layout of an X-33 Full- vehicle Surface Computational Grid 

with Surface Definitions 


h 



Vertical Fin 


Canted Wing 


Outer-Base 
Body-Flap 

Offset Outer-Base 
Inner-Base 
Cowl-Base 


Thrusters 
Plug Side-Wall 
Plug-Base Pillow (Bleed) 


Plug-Base Flex-Seal 






Comparison of Forebody and Aftbody Pressure Coefficients 
with a 7.75% Scaled Model Cold Flow Test 



o 


1.0 

0.8 

0.8 

0.4 

0.2 

0.0 

- 0.2 

- 0.4 

- 0.6 

- 0.8 


O 

O 


1 i 1 i 

ONPR=70, 7.75% cold flow model, M=0.6 

- NPR=92, CFD flgt model, 1803614 pts 

- NPR=92, CFD flgt model, 2131790 pts 

- NPR=92, CFD flgt model, 2217444 pts 



■a 


- 1.0 


0.0 


I 

20.0 


i i 

40.0 60.0 


x/xo 




Comparison of Sea-Level Pillow Pressures with a 
2.25% Scaled Model Hot-Fire Test 



CN 



s- 


-Cl 

CL 



O Qualis 2,25% X33 @P C =669 psia (Ref, 4) 
AQualis 2,25% X35 @P C =71 6 psia (Ref, 4) 
- CFD 100% X33 @P r =669 psia 


3500 


2500 


1500 


1000 


500 


2000 


Distance from centerline, x/x c 


Base pressure ratio, Pbc/PC 


Space Transportation Directorate 


Comparison of Base Characteristic Pressures with a 
2.25% Scaled Model Hot-Fire Test 



0.020 


0.015 


0.010 


0.005 


0.000 



0 


1000 


1 500 5000 6000 


Pressure ratio, PC/Pa 


500 



Space Transportation Directorate 


Comparison of Base Horizontal Centerline Convective Heat 
Fluxes with a 2.25% Scaled Model Hot-Fire Test 




2500 f- 


baseline cases 


2000 - 


OQualis 2.25% X33 @P e =716 psia, P 0 =14.7 psia (Ref. 4) 

— CFD 100% X33 @Pc=857psia, P„=14.7 psia 

— CFP 2.25% X33 (scaled from 100% X33 solution) 


1500 b 

CM 

E 

5 1000 


500 



outer- base inner- base 

O i O , Q- 


-500 


offset 

outer- base 

_l i 


side wall plug -base 




100 


200 

x/x 0 


300 


400 


baseline cases 


T 




AQualis 2,25% X33 ®P C =846 psia, P fl =0.500 psia (Ref. 4) 

- CFD 100% X33 ©P e =857 psia, p fl =0.475 psia 

— CFP 2.25% X33 (scaled from 100% X33 solution) 


400 - 


300 - 


200 - 



700' 

000 

500 


400 


baseline with fence cases 


OQualis 2.25% X33 ©P c =842 psia, P a =0.530 psia (Ref. 4) 

— CFD 100% X33 @P C =857 psia, P.=0.475 psia 

— CFP 2.25% X33 (scaled from 100% X33 solution) 


u 

O 


300 

200 

100 

0 

-100 



. outer- base inner- base 

Q O 




offset 

outer- base 




JL 


side wall plug “base 


100 


200 

x/x 0 


300 


400 


400 


Space Transportation Directorate 


Comparison of Cowl and Inner-Base Radiative Heat 
Fluxes with an Installed Engine Test 




Space Transportation Directorate 


Preliminary Sea Level Qc (KW/m 2 ) Contours 


100% PL 



57% PL 




Ramp 



9000 


O 




Plug-base 



400 


O 





Preliminary Sea Level Qc (KW/m 2 ) Results 


Space Transportation Directorate 


CN 


u 


o 


1100 

1000 

900 

800 

700 

600 

500 

400 

300 

200 

100 

0 

-100 


-Sea level cases 


100% PL 
57% PL 

100% PL wot base- bleed 



offset 

outer-base 


+ | f - 


outer 7 base | inner-baspside wall plu,g-base 


0 


100 


200 

x/x o 


300 





400 


. kW/m 2 Q c . kW/rrv 


Preliminary Sea Level Qc (KW/m 2 ) Results 



Space Transportation Directorate 


X-33 Lower Flex Seal Heat Fluxes 


1000 


900 


800 

700 


400 


300 


200 


1200 

1100 


horizontal line near base- ramp intersection 

■ i 1 l 1 1 — T 1 

100% PL @ SL 



X-33 Lower Flex Seal Heat Fluxes 


X-33 Lower Flex Seal Heat Fluxes 



X-33 Upper Flex Seal Heat Fluxes 



x/x„ 


X-33 Upper Flex Seal Heat Fluxes 


CN 

E 



100% PL 9 SL 

57% PL 0 SL 


horizontal line near middle section 
1200 f 1 1 1 7" 1 1 1 T 


1100 


1000 

900 


300 


200 

100 


800 

700 

800 

500 

400 


100 


E 

\ 

3 


X-33 Upper Flex Seal Heat Fluxes 

horizontal line near ramp -base intersection 


T" 


X 


100% PL 9 SL 
57% PL 9 SL 



Uv/ 


100 - 



20 


40 60 

x/x 0 


80 


100 


x/x c 


80 



Altitude, ft 


PPO Trajectory 


Space Transportation Directorate 






Space Transportation Directorate 


Run Matrix for PPO @ Launch + 30 s 



Case 

t, s 

JVL 

h, ft 

%PL le 

%pl re 

TYIlem 

YYlRE.bb 

1 

0 

0.00 

0 

82 

80 

9.9 

9.7 

2 

30 

0.44 

9495 

100 

100 

12.1 

12.2 

3 

40 

0.37 

13821 

49 

48 

9.0 

2.9 

4 

100 

0.21 

28954 

50 

49 

9.1 

3.0 

5 

200 

1.39 

77217 

51 

48 

9.1 

3.0 

6 

280 

5.00 

168498 

46 

40 

7.9 

2.6 


Base-bleed Vectors after a PPO 



Space Transportation Directorate 








Preliminary Qc Contours for PPO @ Launch + 30 s 


Os 


30 s 


40 s 





100 s 


200 s 


280 s 




Space Transportation Directorate 


Preliminary Qc Results for PPO @ Launch + 30 s 

base horizontal centerline 



500 


400 

CN 

E 

500 

v/ 


V 

200 

U 

o 

100 


o 

-100 


Os on PPO @ L+30s 
30s on PPO @ L+30s 
40 s on PPO @ L+30s 
100s on PPO @ L-l-3Qs 
200s on PPO ® L+30s 
280s on PPO @ L+30s 



0,B QOB , IB | PSW plug-bqse ^ psy/ |p QQB , Oq 




0 100 200 300 400 500 600 700 



Preliminary Qc Results for PPO @ Launch + 30 s 


Space Transportation Directorate 



X-33 Lower Flex Seal Heat Fluxes 

horizontal line near middle section 



E 


a 


180 


1200 

1100 

1000 

900 

800 

700 

S00 

500 

400 

300 

200 

100 

0 


X-33 Upper Flex Seal Heat Fluxes 

horizontal line near middle section 


0s on PPO ® L+30s 
30s on PPO ® L+30s 
40 s on PPO ® L+30s 
100s on PPO ® LH-30s 
200s on PPO ® L+30s 
280s on PPO ® L+30s 






i ai. 


f"7~l~~7"~7" 7 ~ f~ 7 n ~ i 


20 40 


60 


80 100 
x/x 0 


120 140 160 180 


Summary 


A systematically anchored computational fluid dynamics and heat 
transfer model is being used to study the effect of reduced power level 
on base-heating environment during sea level testing and during PPO. 

Preliminary results show that convective heating is higher for 57% PL 
than that for 100% PL on most of the pillows and flex seals during sea 
level testing. This agrees with test observations. 

Preliminary results of PPO @ L +30 s show that convective heating on 
pillows and flex seals on the “off’ engine side is higher than that on 
the “on” engine side. 

Future work includes study of PPO @ L + 60 s and PPO @ L + 120 s 
trajectories to bracket the heating envelope and radiative heating 
calculations.