Data obtained during a wind tunnel test of an 0.004-scale 140A/B configuration SSV Orbiter are reported. The test was conducted at a nominal Mach number of 20 and at Reynolds numbers of 0.7, 1.1, 2.0, and 4 x 10 to the 6th power per foot. The complete 140A/B model was tested with various elevon settings and additionally in wing off/bodyflap off configurations at angles of attack from 18 to 54 degrees at zero yaw. This test was performed to obtain high hypersonic longitudinal and lateral-directional stability and control characteristics of the SSV configuration. (Author)
Results of Investigations on an 0.004-Scale 140A/B Configuration Space Shuttle Vehicle Orbiter Model (34-0) in the NASA/Langley Research Center Hypersonic Helium Tunnel (OA88)
1974
74 pages
Report
No indication
English