Tests were conducted in the AEDC/VKF Hypersonic Wind Tunnel (B) to obtain heat-transfer rate measurements in the elevon/elevon and elevon/fuselage gap areas of the Space Shuttle Orbiter. Data were obtained at Mach 8 over a Reynolds number range from 0.5 to 3.7 million per foot. Angles of attack of 30, 35, and 40 deg were run for yaw angles of 0 and 1 deg. (Author)
Wind Tunnel Tests of Elevon Gap Heating on the Space Shuttle Orbiter (OH-107)
1981
27 pages
Report
No indication
English
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