Approximate theories for supersonic and hypersonic flow over bodies of revolution at zero angle of attack are appraised by comparison with characteristics and second-order results, using hypersonic similarity as basis; combination of second-order supersonic and second-order shock-expansion theory provides good results; summary design curves give pressure drag of conical and ogive noses and boattails over transonic, supersonic, and hypersonic Mach numbers.


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    Title :

    Summary of supersonic pressure drag of bodies of revolution


    Additional title:

    J Aerospace Sciences


    Contributors:

    Published in:

    Publication date :

    1961


    Size :

    10 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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