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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Wind tunnel test of the 0.019 scale space shuttle integrated vehicle (model 14-OTS) in the CALSPAN 8-foot transonic wind tunnel (IA36), volume 2
A test is presented which was performed to determine the effect of cold jet gas plumes generated from main propulsion system and solid rocket motor nozzles on: (1) six-component force and moment data, (2) wing static pressures, (3) wing hinge moment, (4) elevon hinge moment, (5) rudder hinge moment, and (6) orbiter MPS nozzle pressure loads. The effects of rudder deflection, nozzle gimbal angle, and plume size were also obtained.
Wind tunnel test of the 0.019 scale space shuttle integrated vehicle (model 14-OTS) in the CALSPAN 8-foot transonic wind tunnel (IA36), volume 1
For abstract, see N76-13183.
Results of a pressure loads investigation on a 0.030-scale model (47-OTS) of the integrated space shuttle vehicle configuration 5 in the NASA Ames Research Center 9 by 7 foot leg of the unitary plan wind tunnel (IA81B), volume 1
The investigations of pressure distributions are presented for aeroloads analysis at Mach numbers from 1.55 through 2.5. Angles of attack and sideslip varied from -6 to +6 degrees. Photographs of wind tunnel models are shown.
Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 by 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 1
Results of wind tunnel tests on a 0.030-scale model of the integrated space shuttle vehicle configuration 5 are presented. Testing was conducted in the NASA Ames Research Center 11 x 11 foot leg of the Unitary Plan Wind Tunnel to investigate pressure distributions for airloads analyses at Mach numbers from 0.9 through 1.4. Angles of attack and sideslip were varied from -6 to +6 degrees.
Results of a Pressure Loads Investigation on a 0.030-scale Model (451-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 by 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 2
Tabulated force data and plotted pressure data are presented on a scale model of the integrated space shuttle vehicle configuration. For Vol. 1, see N76-15246.
Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 x 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 3
Tabulated pressure data are presented on the orbiter fuselage and left vertical tail surface of a scale model of the integrated space shuttle configuration. For Vol. 1, see N76-15246.
Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 x 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 4
Tabulated pressure data are presented on the left lower wing surface of a scale model of the integrated space shuttle configuration. For Vol. 1, see N76-15246.
Results of a pressure loads investigation on a 0.030-scale model (47-OTS) of the integrated space shuttle vehicle configuration 5 in the NASA Ames Research Center 11 x 11 foot leg of the unitary plan wind tunnel (IA81A), volume 5
Tabulated pressure data are presented on the left upper wing surface of the integrated space shuttle vehicle configuration. For Vol. 1, see N76-15246.
Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 x 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 6
Tabulated pressure data are presented on the right upper wing surface, right lower wing surface, and SRM booster of the integrated space shuttle vehicle configuration. For Vol. 1, see N76-15246.
Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 x 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 7
Tabulated pressure data are presented on the external tank and miscellaneous orifices of the integrated space shuttle vehicle configuration. For Vol. 1, see N76-15246.
Heat transfer tests on a 0.01-scale Rockwell configuration 3 space shuttle orbiter and tank (37-OT) in the Calspan 48-inch hypersonic shock tunnel (OH12/IH21), volume 1
Model information and data are presented from wind tunnel tests conducted on 0.01-scale models of the space shuttle orbiter and external tank. These tests were conducted in a hypersonic shock tunnel to determine heating rates on ascent and reentry configurations at various Reynolds numbers, Mach numbers, and angles of attack.
Heat transfer tests on a 0.01-scale Rockwell configuration 3 space shuttle orbiter and tank (37-OT) in the Calspan 48-inch hypersonic shock tunnel (OH12/IH21), volume 2
Data figures are presented for wind tunnel tests conducted on scale models of the space shuttle orbiter and external tank.