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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Postflight Apollo command module aerodynamic simulation tests


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :