Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehicle configurations for orbiter alone, tank alone, and orbiter plus external tank are presented. Body flap shielding of SSME's during simulated entry was investigated. The tests were conducted at Mach 8 for thirteen Reynolds number. (Author)
Data Report for Tests on the Heat Transfer Effects of the 0.0175 Scale Rockwell International Space Shuttle Vehicle Model 22-Ot in the AEDC 50 Inch B Wind Tunnel (0H4B), Volume 1
1975
652 pages
Report
Keine Angabe
Englisch