A comprehensive postflight wind tunnel investigation of the Apollo Command Module was conducted to resolve several anomalies between flight (AS-202) and preflight aerodynamic data. Attention was focused on (1) simulating the actual vehicle 'as flown', (2) obtaining consistent pitch plane force measurements in the angle-of-attack range 150 < or = alpha < or = 180 deg, (3) the effect of Mach number over a range of 3 to 20, (4) the effect of Reynolds number, and (5) possible sting effects. Results indicated that prior failure to duplicate the asymmetrical wavy heat shield in preflight testing resulted in a significant error in trim angle-of-attack prediction. In addition, a strong viscous influence was found to extend down to an altitude of about 220,000 ft. Also, a Mach number influence to a value of about 14 was found which is substantially higher than previous blunt body investigations have indicated. (Author)


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    Title :

    Postflight (As-202) APOLLO Command Module Aerodynamic Simulation Tests


    Contributors:

    Publication date :

    1968


    Size :

    113 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English