Calculation of pressure distribution along spanwise strip of airfoil due to angle of attack along second spanwise strip; results of earlier papers used to calculate lift and moment coefficients for rectangular airfoil that experiences sudden change in angle of attack (without rotation) in otherwise uniform supersonic stream or which enters sharp edged gust; results are valid when Mach lines from leading edge corners do not intersect opposite side edges; curves.


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    Title :

    Transient loading of supersonic rectangular airfoils


    Additional title:

    J Aeronautical Sciences


    Contributors:
    Miles, J.W. (author)

    Published in:

    Publication date :

    1950


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Transient loading of airfoils at supersonic speeds

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