Tests were conducted in wind tunnels during April and May 1973, 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 investigation included tests on the integrated (launch) configuration and on the isolated orbiter (entry configuration). The integrated vehicle 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. Tabulated pressure data are presented for: orbiter fuselage and base, upper MPS nozzle, OMS nozzle, body flap, OMS pod outside, and lower wing surface. (Author)


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    Title :

    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 11


    Contributors:

    Publication date :

    1973


    Size :

    819 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English