Effects of nose shape, afterbody shape, fineness ratio, and transition strips are presented at several subsonic Mach numbers through angle of attack range from -- 4 to 24°; applicability to recoverable low lift vehicles capable of atmospheric entry at high speeds.


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    Title :

    Some effects of nose bluntness and fineness ratio on static longitudinal aerodynamic characteristics of bodies of revolution at subsonic speeds


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    65 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English