An approximate solution is reported for the unsteady aerodynamic response of an infinite swept wing encountering a vertical oblique gust in a compressible stream. The approximate expressions are of closed form and do not require excessive computer storage or computation time, and further, they are in good agreement with the results of exact theory. This analysis is used to predict the unsteady aerodynamic response of a helicopter rotor blade encountering the trailing vortex from a previous blade. Significant effects of three dimensionality and compressibility are evident in the results obtained. In addition, an approximate solution for the unsteady aerodynamic forces associated with the pitching or plunging motion of a two dimensional airfoil in a subsonic stream is presented. The mathematical form of this solution approaches the incompressible solution as the Mach number vanishes, the linear transonic solution as the Mach number approaches one, and the solution predicted by piston theory as the reduced frequency becomes large. (Author)


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    Titel :

    The Passage of an Infinite Swept Airfoil Through an Oblique Gust


    Beteiligte:
    J. L. Adamczyk (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    100 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






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