Tabulated pressure data were obtained for the following components: APU inlet, SRM booster base, and external tank and tank base. For complete abstract, see . included tests on the integrated (launch) configuration and the isolated orbiter (entry configuration). 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. Tabulated pressure data were obtained for upper and lower wing surfaces and left and right vertical tail surfaces. (Author)


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    Titel :

    Results of Tests OA12 and IA9 in the Ames Research Center Unitary Plan Wind Tunnels of a 0.030-Scale Model of the Space Shuttle Vehicle 2A to Determine Aerodynamic Loads, Volume 15


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

    Erscheinungsdatum :

    1974


    Format / Umfang :

    912 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch