Wind-tunnel investigation was conducted 1) to simulate actual vehicle "as flown" (AS-202) in model construction, 2) to obtain consistent pitch plane force measurements in angle-of-attack range 150° equal to or less than α equal to or less than 180°, 3) to determine effects of Mach number (from 3 to 20) and Reynolds number, and 4) to evaluate possible sting effects; study showed that influence of ablator (heat shield) geometry prior to ablation causes significant change in trim angle of attack and resulting decrease in available lift-to-drag ratio.


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    Titel :

    Postflight Apollo command module aerodynamic simulation tests


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Griffith, B.J. (Autor:in) / Boylan, D.E. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1968


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :