The geared flap control system provides a means for controlling a tiltwing V/STOL aircraft in hover and transition flight without the use of auxiliary systems such as cyclic propeller pitch or tail jets/rotors. The system is based on using the flap as an aerodynamic servo to position the wing relative to the fuselage. Although the system is mechanically simple, the control characteristics are difficult to visualize because of the coupled body dynamics involved. Therefore, a comprehensive...

Topics: DTIC Archive, Churchill, G B, BOEING VERTOL CO PHILADELPHIA PA, *FLAPS(CONTROL SURFACES), *FLIGHT...

Wind tunnel tests were conducted on a 0.25-scale model to determine the static stability and control characteristics of the Super HOBOS/MK-84 (EOGB- II) munition. The tests were performed in the Aerodynamic Wind Tunnel (4T) over a Mach number range from 0.4 to 1.6 at angles of attack from -4 to 26 deg. Aerodynamic coefficients and control effectiveness data are presented. Two techniques, one using multiple flap deflections and the other single flap deflections, were employed during the test. A...

Topics: DTIC Archive, Smith, D K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *GUIDED BOMBS,...

It is shown that aerodynamic interference can produce unsteady flow over a fixed airfoil up to reduced frequencies of 6.4. The resulting pressure distributions are well behaved, repeatable and, within limits, predictable. Further it is shown that the resulting boundary layer velocity profile can be measured with the same precision as in the steady flow.

Topics: DTIC Archive, Lorber, Peter F, MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB, *AIRFOILS,...

A parallel plate electrostatic analyzer (ESA) to detect 0.08 to 17 keV electrons was launched on the S3-2 satellite in late 1975. Analysis of the low altitude data revealed that the ESA was responding to the neutral atmosphere through a ram effect. The ram effect was confined to attack angles of less than about 30 deg, and was generally present only at the lowest altitudes (250-300 km). By excluding all data with an ESA attack angle of less than 45 deg, completely reliable electron spectra are...

Topics: DTIC Archive, Hanser,Frederick A, PANAMETRICS INC WALTHAM MASS, *ELECTRON SPECTROSCOPY,...

Finding guidance methods that efficiently and effectively handle the problem of directing the boost-phase portion of an exoatmospheric tactical ballistic missile interceptor is an active area of research. This paper presents a candidate method that is a hybrid combination of three algorithms. The chief method, used throughout the majority of the flight, is a minimum-time neighboring optimal control scheme. As demonstrated through Monte Carlo simulations, perturbations in the predicted intercept...

Topics: DTIC Archive, Lawton, John A., NAVAL SURFACE WARFARE CENTER DAHLGREN DIV VA, *BALLISTIC MISSILE...

The flowfield about a vertically-launched surface-to-air missile model at an angle of attack of 50 degrees and a Reynolds number of 1.1x10(5) was investigated in a low-speed wind tunnel at the Naval Postgraduate School. Determined were the location and intensity of the asymmetric vortices in the wake of the model using planar velocity vector, total pressure coefficient, and vorticity plots. Two model configurations were tested: one at a roll angle of 0 degrees (the \"+\"...

Topics: Vertical launch, Surface-to-air missile, High angle of attack aerodynamics, Turbulence, Body of...

An improved panel method for the solution of three dimensional flow and wing and wing-body combinations with leading edge vortex separation is presented. The method employs a three dimensional inviscid flow model in which the configuration, the rolled-up vortex sheets, and the wake are represented by quadratic doublet distributions. The strength of the singularity distribution as well as shape and position of the vortex spirals are computed in an iterative fashion starting with an assumed...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, LEADING EDGES, VORTICES, ANGLE...

Wind tunnel tests were conducted to determine the low speed, two dimensional aerodynamic characteristics of a 13percent thick medium speed airfoil designed for general aviation applications. The results were compared with data for the 13 percent thick low speed airfoil. The tests were conducted over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle of attack frange from about -8 deg to 10 deg. The...

Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, ANGLE OF ATTACK, GENERAL AVIATION AIRCRAFT,...

The report presents the results of an experimental investigation of the dynamic airloads on an airfoil (Vertol 23010-1.58) immersed in reverse flow such as occurs on the retreating side of a helicopter rotor disc in forward flight. Forces and moments in two-dimensional flow were determined from airfoil differential pressures measured during pitching oscillation. Mach number, Reynolds number, and mean angle-of-attack ranges corresponded to those typically encountered under full-scale flight...

Topics: DTIC Archive, Gray, Lewis, BOEING VERTOL CO PHILADELPHIA PA, *AIRFOILS, *SECONDARY FLOW,...

Separation trajectory data were obtained to investigate some possible ways to reduce the nose-down pitch of the SUU-51B/B store during separation from the Triple Ejection Rack (TER) on the F-4C aircraft. Data were obtained to assess the influence on the store separation characteristics resulting from (1) changing the store mass properties (ballasting), (2) modifying the TER geometry to represent removal of the nose fairing, (3) changing the store carriage location on the TER, (4) modifying the...

Topics: DTIC Archive, Summers, Willard E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *EXTERNAL...

Thermographic phosphor heat-transfer tests were made on two models (0.5-scale and 0.25-scale) of the High Altitude Supersonic Target (HAST) missile at Mach number 4 and a Reynolds number, based on model length, of 21 million. Angle of attack was varied from 0 to 12 deg; effects of canard settings of 0 and 15 deg for the 0.25-scale model and 0, 5, 10, and 15 deg for the 0.5-scale model were examined. Comparisons of results by heat-transfer gages, thermographic phosphor, and surface thermocouple...

Topics: DTIC Archive, Knox, E C, ARO INC ARNOLD AFS TN, *HEAT TRANSFER, *PAINTS, *TARGET DRONES, AERIAL...

A method is described by which concentration distortion of particulates of arbitrary sizes caused by airflow around airplane fuselages can be calculated. The method accounts for effects of: three-dimensional details of the fuselage shape on airflow, angle-of-attack on airflow, altitude, interaction of the particles with the airflow, and particle settling. It has been applied to hydrometeor sampling instruments on three cloud physics airplanes: Lockheed C130A and C130E transports, and a Cessna...

Topics: DTIC Archive, Norment, Hillyer G, MOUNT AUBURN RESEARCH ASSOCIATES INC NEWTON UPPER FALLS MA,...

An experimental test program was conducted in the AEDC-VKF Hypervelocity Wind Tunnel (F) at a nominal Mach number of 16 to obtain basic heating and pressure distribution data on the NASA Space Shuttle external tank. The tests were conducted over an attitude range which simulated tank tumbling after separation from the Shuttle orbiter. The angles of attack varied from 0 to -180 deg with combinations of roll from 0 to 90 deg at free-stream Reynolds numbers (based on model length) from 0.38 x...

Topics: DTIC Archive, Siler, L G, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AERODYNAMIC...

A large body of wind tunnel data was generated by tests of a smooth missile model with several interchangeable nose parts. The tests were conducted at subsonic through supersonic speeds at angles of attack from 0 to 180 degrees. They were part of the FDL and SAMSO technology studies which preceded design of the MX missile. Measurements of both surface pressures and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with...

Topics: DTIC Archive, Dahlem, Valentine, AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH, *GUIDED...

A wind tunnel investigation was conducted to determine the effect of leading edge modifications on the stall characteristics of a swept planform wing. The modifications consisted of openings in the leading edge which generated a vortex pattern over the wing surface. The force/moment results showed that a 33 percent increase in stall angle of attack could be achieved with the leading edge modifications. A maximum lift coefficient comparable to that of the baseline wing was also achieved with the...

Topics: DTIC Archive, Van Gunst, Roger W, MICHIGAN UNIV ANN ARBOR AIRCRAFT RESEARCH LAB, *SWEPT WINGS,...

An experimental study has been carried out in which the effect of tip bluntness on the turbulent boundary layer over an axisymmetric body was examined. It was performed at a Mach number of 2.94 with a unit Reynolds number of roughly 6.34 x 10 to the 7th power per meter and a nearly adiabatic wall condition. A tangent ogive-cylinder was used with a noise fineness ratio of approximately 3. Six model tips were constructed with hemispherical and flat blunting of various dimensions. In addition, to...

Topics: DTIC Archive, Gray,William K, PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING,...

Excellent high-lift and cruise performance of a small, round, fixed circulation control wing (CCW) trailing edge fitted to a supercritical airfoil has been confirmed by subsonic wind tunnel investigations. This fixed-trailing- edge blown high-lift airfoil generates a negligible subsonic cruise drag penalty, but can generate a section lift coefficient near 7.0. This configuration is a significant improvement over the flight-proven A-6/CCW airfoil that had similar lift performance, but had a...

Topics: DTIC Archive, Englar, Robert J, DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA...

This work applies the Woodward USSAERO C code in a shortened form to the loads on an airfoil in the downwash field of a forward airfoil including the vortex impingement. The calculated pressure distributions are in general agreement with the experimental data, although both show the influence of the forward airfoil to be small in this case of a not-too-closely coupled line. The general trends of the loading on the rear fin both inboard and outboard of the vortex impingement are well...

Topics: DTIC Archive, Maddox, Arthur R, NAVAL ACADEMY ANNAPOLIS MD DIV OF ENGINEERING AND WEAPONS,...

Measurements of cloud particle images and concentrations using laser spectrometers housed in pods mounted on the wings or fuselages of research aircraft can be affected by the distortion of the airflow about the aircraft. The Flight Research Laboratory has developed a pod with a Rosemount 858 5-hole probe and pressure transducers to measure airflow angles and velocities at typical mounting locations on cloud physics research aircraft. This report documents the results of an extensive wind...

Topics: DTIC Archive, MacPherson,J I, NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), *LASER BEAMS,...

This thesis sought to develop nonlinear systems analysis techniques capable of analyzing and predicting the complex behavior found in high-angle-of-attack flight. The primary research method involved calculation of equilibrium surfaces where the time rate of change of each of the state variables is set to zero in the aircraft equations of motion, and the states that will satisfy that condition are found for various control deflections. The equilibrium surfaces were calculated numerically...

Topics: DTIC Archive, Hawkins,Carl A, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH, *EQUATIONS OF MOTION,...

The dynamic stall of rapidly pitching and oscillating airfoils is investigated by the numerical solution of the full compressible unsteady two- dimensional Navier-Stokes equations using an alternating-direction-implicit scheme. The flow is assumed to be fully turbulent, and the turbulent stresses are modelled by the Baldwin-Lomax eddy viscosity model. Three airfoils (NACA 0012, NACA 0012-33, and NACA 0012-63) are analyzed for the purpose of examining the influence of leading-edge geometry on...

Topics: DTIC Archive, Grohsmeyer, Steven P, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *AIRFOILS, *STALLING,...

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to...

Topics: DTIC Archive, Pettit, Chris, WRIGHT LAB WRIGHT-PATTERSON AFB OH, *BUFFETING, *UNSTEADY FLOW, TEST...

Topics: DTIC Archive, Ribner, Herbert S., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY...

A piloted experimental study of potential enhanced task performance resulting from improved high angle-of-attack aerodynamic and flight control capability was conducted in the Air Force Research Laboratory's engineering flight simulator facility. The simulation database used was representative of the aerodynamics and inertias of the Variable-stability In-flight Simulator Test Aircraft (VISTA)/F-16. The VISTA variable-stability control laws were not used. Three flight test pilots evaluated both...

Topics: DTIC Archive, McKeehen, Phillip D., WRIGHT LAB WRIGHT-PATTERSON AFB OH, *FLIGHT CONTROL SYSTEMS,...

Topics: DTIC Archive, ARABIAN, DONALD D., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, NAVAL RESEARCH LAB WASHINGTON DC, *JET FIGHTERS, MANEUVERABILITY, EQUATIONS OF...

The aerodynamic wind tunnel test program for the FDL-5 configuration is described in this Part III. The description includes the models, test facilities, data reduction and presentation, and the test schedules. A complete presentation of the aerodynamic test data is provided. The data include six component force and moment data, pressure data, and photographic data for the Mach number range between 1.5 to 20. Correlations between the data and appropriate theories are presented. The overall...

Topics: DTIC Archive, Ehrlich, Carl F, LOCKHEED-CALIFORNIA CO BURBANK, *LIFTING REENTRY VEHICLES,...

The evolution of unsteady boundary layers on the plane of symmetry of a slender prolate spheroid in uniform motion at constant angle of attack after an impulsive start has been studied for the case of prescribed pressure distribution. Calculated results have been obtained for angles of attack ranging from 30 degrees to 50 degrees and show, for example, that the unsteady-state solutions approach the steady-state solutions rapidly on the windward and leeward sides for alpha and alpha sub c...

Topics: DTIC Archive, Cebeci,T, MCDONNELL DOUGLAS CORP LONG BEACH CA, *BOUNDARY LAYER, *UNSTEADY FLOW,...

A need has emerged for numerical schemes to predict hypersonic flows around three-dimensional configurations. The Army has shown considerable interest in applying 3-D PNS schemes to study supersonic/hypersonic flowfields around projectiles and missiles. Although the existing noniterative PNS schemes offer an attractive combination of accuracy and affordability, such schemes suffer from several numerical instability and inaccuracy problems. This study develops a new 3-D PNS scheme with...

Topics: DTIC Archive, Bhutta, Bilal A, VRA INC BLACKSBURG VA, *NAVIER STOKES EQUATIONS, *HYPERSONIC FLOW,...

Stroboscopic schlieren photography was used to investigate the effects of compressibility, reduced frequency, and amplitude on the dynamic stall of a NACA 0012 airfoil subjected to sinusoidal oscillation. The Mach number was varied from M at infinity = 0.25 to M at infinity = 0.45 (corresponding to a Reynolds number variation of Re = 450,000 to Re = 810,000); the reduced frequency was varied from k = 0.025 to k = 0.10. Oscillation amplitudes of alpha sub m = 5 deg and alpha sub m = 10 deg were...

Topics: DTIC Archive, Brydges, Bruce E, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *FLOW VISUALIZATION,...

The location of three-dimensional separation on bodies such as submarines is important diagnostic information. Considerable changes in the side forces and moments occur with the undesirable phenomenon of separation. Three- dimensional flow separations occur very close to local minima in the magnitude of the wall shear stress. A 1000-flush-surface-sensor constant-current- anemometer separation location system is described here for locating these local minima along the axis of a body. As shown...

Topics: DTIC Archive, Simpson, R L, JASON ASSOCIATES CORP DEL MAR CA, *FLUID FLOW, *FLOW SEPARATION,...

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to...

Topics: DTIC Archive, Pettit, Chris, WRIGHT LAB WRIGHT-PATTERSON AFB OH, *AERODYNAMIC CHARACTERISTICS,...

A new technique using a multi-flash x-ray system has been developed to measure projectile striking velocity, angle of yaw at impact, plastic flow properties at the projectile/target interface, penetration time, and the amount and direction of material emerging from the rear surface of the target.

Topics: DTIC Archive, Grabarek, Chester L, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD,...

This document was prepared as a part of the Supersonic Transport (SST) contract. The objective was to evaluate the suitability of fifteen selected domestic U. S. airports to accommodate the Boeing 2707. The various compatibility aspects of the study were calculated and results superimposed over aerial photographs of the various airports and their terminals. Cost estimates necessary to upgrade the airports to a state of minimum compatibility with the SST are also displayed.

Topics: DTIC Archive, BOEING COMMERCIAL AIRPLANE CO RENTON WA, *JET TRANSPORT AIRCRAFT, *AIRCRAFT LANDINGS,...

A test program was conducted in the Propulsion Wind Tunnel (16T) to determine forces and moments on a 1/24-scale F-111 model. Data were obtained at Mach numbers from 0.7 to 1.3 at total pressures of 1200 and 2000 psfa. Model angle of attack was varied from -2 to 20 deg at 0-deg sideslip. Sideslip angles were varied from -10 to 10 deg at 10- and 15-deg angles of attack. (Author)

Topics: DTIC Archive, Burchfield,C G, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN, *AERODYNAMIC...

This report documents a demonstration calculation performed to evaluate the three-dimensional Eulerian/Lagrangian linked hydrocode developed under this contract. The calculation consists of a staballoy rod impacting an armor plate at obliquity 65 degrees and velocity 1 km/sec. Calculational results compared favorably with experimental data. The linked calculation was completed with the use of about nine total CDC 7600 computer hours as compared to the estimated 25 hours if the calculation had...

Topics: DTIC Archive, Matuska, Daniel A., ORLANDO TECHNOLOGY INC SHALIMAR FL, *HYDRODYNAMIC CODES, *ARMOR...

This technical information memorandum presents the results and data from wind tunnel calibration of the flow-angle sensing portion of the Air Force Flight Test Center noseboom instrumentation unit. Analysis of the data from the NASA/Ames Research Center 11- by 11-foot and 9- by 7-foot wind tunnels is presented along with fairings resulting from the analysis. The data fairings, which present error in sensed angle of attack and sensed angle of sideslip as a function of Mach number, angle of...

Topics: DTIC Archive, Rawlings,Kenneth , III, AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA, *Aeronautical...

The present study assesses real gas effects in the prediction of flow- fields over Army projectiles. Solutions are obtained for a spherically tipped cone-cylinder model flying at three different flight conditions. Real gas effects may be important for the pressure and heat transfer on the spherical tip. Real gas effects are not important for the prediction of pressure and heat transfer on the region of the model aft of the spherical tip.

Topics: DTIC Archive, Nicolet,W E, THERMAL SCIENCES INC SUNNYVALE CA, *Hypersonic flow, *Kinetic energy...

Parametric low-speed wind tunnel testing of several low aspect ratio half-span wings featuring outboard-blowing wing-tip jets has been accomplished. This effort was performed to extend the existing information base regarding lift augmentation of low aspect ratio wings to encompass tapered wings suitable for application to high-performance fighter aircraft. At an angle of attack typical for fighter aircraft takeoff, operation of the wing-tip jets was found to augment the lift coefficient of...

Topics: DTIC Archive, Schwind,R G, NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA, *Wings, *Jet...

Supersonic wind-tunnel tests were conducted with disk-gap-band parachute models having a nominal diameter of 1.65 meters and geometric porosities of 10.0, 12.5, and 15.0 percent. Canopy inflation characteristics, angles of attack, and drag performance are presented for deployment behind forebody base extensions which were free to oscillate in pitch and yaw. The effect of increasing suspension-line length on canopy motions and drag performance is included, and the drag performance of a model...

Topics: NASA Technical Reports Server (NTRS), ANGLE OF ATTACK, PARACHUTES, SUPERSONIC DRAG, WIND TUNNEL...

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch Trisonic Wind Tunnel on a 0.004-scale model of the NR ATP baseline Shuttle launch configuration. The test model consisted of the NR ATP baseline orbiter, external tank, and SRB's with nozzles. Six component aerodynamic force and moment data were recorded over an angle of attack range from minus 10 deg to 10 deg at zero degrees sideslip and angle of sideslip range of minus 10 deg to 10 deg at zero angle of attack for...

Topics: NASA Technical Reports Server (NTRS), SCALE MODELS, SPACE SHUTTLE ASCENT STAGE, SPACE SHUTTLES,...

This report presents the results of an investigation to use viscous computational fluid dynamic calculations to predict the flowfleld and aerodynamic coefficients for a missile with grid fins in the supersonic flow regime. The calculations were made at Mach 2 and 3 and several angles of attack. The results were validated by compamig the computed aerodynamic coefficients against wind tunnel experimental data. Good agreement was found between the computed and experimental axial force...

Topics: DTIC Archive, DeSpirito, James, ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD, *COMPUTATIONAL FLUID...

The flow control methods being exploited by Micro-electro-mechanical systems (MEMS) devices rely in many cases on the manipulation of small-scale vortices to provide favorable mixing effects. By appropriate design and siting of MEMS very local effects on the flow can be made to provoke large-scale changes in the flow structure and, for example, control the conditions at which the flow separates. This topic area will not be considered further in this paper, but results from current research...

Topics: DTIC Archive, Lovell, D A, QINETIQ LTD FARNBOROUGH (UNITED KINGDOM), *VORTICES, *ANGLE OF ATTACK,...

A passive wingtip load alleviation system was devised, tested, and analyzed for its effect on the reduction of structural deformations and the extension of flutter speed. The sensors responded to changes in angle of attack and vertical movement of the wingtip and were used to deflect a trailing edge flap to alleviate the induced loads.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, FLUTTER ANALYSIS, WING TIPS, ANGLE OF...

For abstract, see N75-13822.

Topics: NASA Technical Reports Server (NTRS), LOADING MOMENTS, SCALE MODELS, SPACE SHUTTLE ORBITERS, WIND...

Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, LAUNCH VEHICLE CONFIGURATIONS, SPACE...

Pressure data are presented in tabular form on the external tank base and SRM booster base of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, LAUNCH VEHICLE CONFIGURATIONS, SPACE...

A study was made of the upwash interference caused by the wind tunnel walls at a Mach number of 0.20. The wind tunnel has slotted horizontal walls and solid vertical walls and the wind tunnel model is a wing-fuselage combination typical of a short take-off and landing (STOL) transport. Measurements were made of the model forces and angle of attack. The experimental results are compared to theoretical solutions for the upwash interference. This comparison enabled an indirect determination of one...

Topics: NASA Technical Reports Server (NTRS), INTERFERENCE LIFT, SHORT TAKEOFF AIRCRAFT, SLOTTED WIND...

For abstract, see N76-13185.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, PRESSURE DISTRIBUTION, SCALE MODELS, SPACE...

A Rockwell built 0.030-scale 45-0 modified Space Shuttle Orbiter Configuration 14?A/B model and a Boeing built 0.030-scale 747 carrier model were tested to provide six component force and moment data for each vehicle in proximity to the other at a matrix of relative positions, attitudes and test conditions (angles of attack and sideslip were varied). Orbiter model support system tare effects were determined for corrections to obtain support-free aerodynamics. In addition to the balance force...

Topics: NASA Technical Reports Server (NTRS), BOEING 747 AIRCRAFT, SCALE MODELS, SPACE SHUTTLE ORBITERS,...