Tabulated pressure data are presented for: upper wing surface, left and right verticle tail surfaces, APU inlet, SRM booster and booster base, and external tank and tank base. For complete abstract, see . 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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    Titel :

    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 12


    Beteiligte:
    R. H. Spangler (Autor:in)

    Erscheinungsdatum :

    1973


    Format / Umfang :

    1179 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch