Space Shuttle Integrated Vehicle Aerodynamic Interference Heating Test (NASA JSC Test IH-97)
Final rept. Aug-Dec 1982
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Wind tunnel tests were conducted on the 0.0175 scale 60-OTS integrated Space Shuttle Vehicle in the von Karman Gas Dynamics Facility Tunnel A. The objectives were to obtain heating data in locations where developmental flight instrumentation DFI had been placed on the full scale vehicle and to obtain validation data for the aeroheating design methodology. Data were obtained over the Mach range of 2.25 to 4.00 at free stream unit Reynolds numbers of 3.7 x 10.6 to 5.7 x 10.6 per foot. Model attitude was varied over the range 5 to -5 degrees angle of attack and 6 to -6 degrees angle of side slip.
- Test Facilities, Equipment and Methods
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry