Tests were conducted in the NASA/ARC Unitary Plan Wind Tunnels on an 0.030 scale replica of the space shuttle vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -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 0A12 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 16
1974
934 pages
Report
Keine Angabe
Englisch