WIND TUNNEL TESTS OF THE 0.010-SCALE SAPCE SHUTTLE INTEGRATED VEHICLE (MODEL 52-0T) IN THE NASA/AMES 3.5-FOOT HYPERSONIC WIND TUNNEL (IA18)

摘要

Experimental aerodynamic investigations were conducted in the NASA/ Ames Research Center 3.5-foot Hypersonic Wind Tunnel from April 9, 1974 to April 12, 1974 on an 0.010-scale model of the Space Shuttle Integrated Vehicle consisting of an orbiter and external tank (Model 52-OT).nThe purpose of the test was to evaluate the basic hypersonic stability characteristics of the orbiter attached rigidly to the external tank and to evaluate the basic hypersonic stability characteristics of external tank alone simulating RTLS abort conditions. Test IA18 was conducted at Mach numbers of 5.3, 7.3 and 10.3.