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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    Titel :

    Transient loading of supersonic rectangular airfoils


    Weitere Titelangaben:

    J Aeronautical Sciences


    Beteiligte:
    Miles, J.W. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1950


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Transient loading of airfoils at supersonic speeds

    Miles, J.W. | Engineering Index Backfile | 1948



    Airfoils in slightly supersonic flow

    Tsien, H.S. / Baron, J.R. | Engineering Index Backfile | 1949


    Supersonic low-density flow over airfoils

    TAI, TSZE C. / MORAN, MARK S. | AIAA | 1989