For abstract see, . components are included. For complete abstract, see . Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from minus 8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from minus 15 degrees to +40 degrees and angles of sideslip from minus 10 degrees to +10 degrees as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated. (Author)
Results of Tests OA12 and IA9 in the Ames Research Center Unitary Plan Wind Tunnels on an 0.030-Scale Model of the Space Shuttle Vehicle 2A to Determine Aerodynamic Loads, Volume 6
1973
871 pages
Report
No indication
English