Pressure distributions and shock shapes for cylindrical afterbodies were calculated by using method of characteristics for air and helium and Mach number range from 5 to 40; flow parameters obtained from blast wave theory give good correlations of blunt nose induced pressures and shock shapes; concept of hypersonic similitude enables good correlation of results with respect to body shape, Mach number, and ratio of specific heats.


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    Title :

    Analytic study of induced pressure on long bodies of revolution with varying nose bluntness at hypersonic speeds


    Additional title:

    NASA -- Tech Report


    Contributors:


    Publication date :

    1960


    Size :

    37 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :