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Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030-scale model of the Space Shuttle Vehicle 2A to determine aerodynamic loads, volume 12
For abstract, see N74-17569. For complete abstract, see .
Effect of reaction control system jet-flow field interactions on a 0.015 scale model space shuttle orbiter aerodynamic characteristics
The effects of the reaction control system (RCS) jet-flow field interactions on the space shuttle orbiter system during entry are discussed. The primary objective of the test program was to obtain data for the shuttle orbiter configuration to determine control amplification factors resulting from jet interaction between the RCS plumes and the external flow over the vehicle. A secondary objective was to provide data for comparison and improvement of analytic jet interaction prediction techniques. The test program was divided into two phases; (1) force and moment measurements were made with and without RCS blowing, investigating environment parameters (R sub e, Alpha, Beta), RCS plume parameters (Jet pressure ratio, momentum ratio and thrust level), and geometry parameters (RCS pod locations) on the orbiter model, (2) oil flow visualization tests were conducted on a dummy balance at the end of the test.
Supersonic performance, stability and control characteristics of a 0.01875 scale model Rockwell International 089B-139B orbiter configuration (LA8C)
An investigation was made in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.9 and 2.86 to study the supersonic aerodynamic characteristics of a Rockwell International shuttle orbiter configuration. Tests were made at a Reynolds number of 1.5 million per foot with an angle-of-attack range of minus 4 to 28 deg and sideslip variations of minus 6 to 8 deg. The effects of elevon and aileron deflections were investigated.
Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels of a 0.030-scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 15
For abstract, see N74-20529. For complete abstract, see .
Results of tests OA63 and IA29 on an 0.015 scale model of the space shuttle configuration 140 A/B in the NASA/ARC 6- by 6-foot transonic wind tunnel, volume 2
For abstract, see N74-27386.
Results of tests OA63 and IA29 on an 0.015 scale model of the space shuttle configuration 140 A/B in the NASA/ARC 6- by 6-foot transonic wind tunnel, volume 3
For abstract, see N74-27386.
Reynolds number effects on hypersonic characteristics of a 0.010-scale model of the 139-B shuttle orbiter
Longitudinal and lateral-directional stability characteristics of the 139-B orbiter (model 32-0) were obtained in a continuous flow hypersonic tunnel at Mach 10.3. Tests were made at Reynolds numbers of 1.04 million and 2.17 million (based on body length) over an angle of attack range of 12 deg to 36 deg at sideslip angles of 0 deg and minus 5 deg. Data were obtained at three elevon/body flap settings.
Results of tests of a 0.010- and 0.015-scale models of space shuttle orbiter configurations 3 and 3A in the Ames Research Center 3.5 foot hypersonic wind tunnel (OA23)
Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach numbers of 5.3, 7.3 and 10.3 at angles of attack up to 50 degrees with Beta = 0 degrees and, for a few cases, Beta = 5 degrees. Component force data, fuselage base pressures and shadowgraph patterns were recorded.
Longitudinal and lateral stability and control characteristics of a large-scale model with a swept wing and augmented jet flap
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Aerodynamic results of wind tunnel separation tests on a 0.01-scale model (32-OTS) space shuttle integrated vehicle in the AEDC-VKF-SWTA (IA57)
The integrated space shuttle vehicle was tested to determine proximity force and moment data for the orbiter/external tank and solid rocket booster (SRB) with and without separation rockets firing for both single and dual booster runs. Data were obtained at points t = 0 sec, t = 1.25 sec, and t = 2 sec on the nominal SRB separation trajectory.
A hypersonic force and moment test of a 0.006 scale model (466) of the 330.2 inch diameter external tank in the Ames Research Center 3.5 foot hypersonic wind tunnel (TA9F)
Data were obtained in a series of wind tunnel tests on the space shuttle external tank over an angle of attack range from 0 deg to 180 deg at Mach numbers of 5.3 and 10.4. Body roll angles varied from 0 deg to 315 deg for the Mach number 10.4 tests. A constant roll angle of 180 deg was used for all Mach number 5.3 tests. The effects of protuberances and Reynolds number on the force and moment coefficients were investigated.
Aeroacoustic performance of scale model sonic inlets
A low speed wind tunnel was used to evaluate the inflight aeroacoustic performance of several single- and multiple-passage sonic inlets. Takeoff and approach geometries were tested, and the effects of inlet lip and diffuser design were determined. Results indicate that the single passage geometries, in particular a cylindrical centerbody takeoff geometry and a bulb shaped centerbody approach geometry, provide the highest level of aeroacoustic performance. Increasing inlet lip contraction ratio extends the maximum incidence angle for attached lip flow, while increasing inlet diffuser length results in higher total pressure recovery for a given amount of noise suppression.
Triple balance test of the PRR baseline space shuttle configuration on a .004 scale model of the MCR 0074 orbiter configuration in the MSFC 14 x 14 inch Trisonic Wind Tunnel (TWT 570) IA31F(B), volume 1
A wind tunnel force and moment test of the space shuttle launch vehicle was conducted. The wind tunnel model utilized a triple balance such that component aerodynamics of the orbiter, external tank, and solid rocket booster was obtained. The test was conducted at an angle of attack range from -10 deg to 10 deg, and angle of sideslip range from -10 deg to 10 deg, and a Mach number range from 0.6 to 4.96. Simulation parameters to be used in future launch vehicle wind tunnel tests were investigated. The following were included: (1) effect of orbiter -ET attach hardware; (2) model attachment (spacer) effects; (3) effects of grit on model leading surfaces; and (4) model misalignment effects. The effects of external tank nose shape was studied by investigating five different nose configurations. Plotted and tabulated data is reported.
Results from investigations in the NASA/MSFC TWT on a .004 scale model space shuttle launch vehicle (model 13P-OTS) to determine gas supply strut effects on model pressure environment (IA53)
The Rockwell Space Shuttle Launch Vehicle components were tested in a Trisonic Wind Tunnel. Pressure measurements were made on the aft portion, in the base regions, and on the wing surfaces. Axial force determination were made from the pressure data. Data were recorded with the model at zero degrees angle of attack and sideslip through a Mach number from 0.9 to 3.0. The only configuration changes investigated were strut mounting techniques and gas line fairing location between the external tank and the orbiter.