Assumptions underlying application of shock expansion theory to calculation of pressure distribution on thin sharp nosed 2-dimensional airfoil in supersonic stream examined, and it is suggested that they might be expected to lead to appreciable errors when Mach Number is large; this case is examined by use of " hypersonic analogy".


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    Title :

    Critique of shock-expansion theory


    Additional title:

    J Aeronautical Sciences


    Contributors:

    Published in:

    Journal of the Aeronautical Sciences ; 22 , n 10 ; p 673-680 + 720


    Publication date :

    1955


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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