Slender-body theory is combined with higher-order boundary-layer concepts in order to determine the boundary-layer-induced potential flow over wing-body cylindrical cross sections. It is shown that the three-dimensional viscous displacement flowfield can be evaluated, in the vicinity of the surface of the cylinder, by a quasi-two-dimensional slender body procedure. This approximation is valid when the boundary layer is thin, the body is 'slender' in the usual inviscid sense, and there are no geometrical discontinuities. The induced potential flow is determined by conformal mapping techniques. These solutions are obtained in closed form or by quadratures. Complete second-order secondary-flow boundary-layer solutions are obtained for an elliptical fuselage-wing-tail cross section. (Jensen)


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    Titel :

    Boundary-layer-induced secondary flows on wing-body configurations


    Weitere Titelangaben:

    Grenzschichtinduzierte Sekundaerstroemungen an verschiedenen Tragfluegel- und Rumpfformen und deren Zusammenwirkung


    Beteiligte:
    Rubin, S.G. (Autor:in) / Lyons, J.M. (Autor:in)

    Erschienen in:

    AIAA Journal ; 18 , 1 ; 55-62


    Erscheinungsdatum :

    1980


    Format / Umfang :

    8 Seiten, 10 Bilder, 11 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





    Boundary layer induced secondary flows due to wing-body interference

    Rubin, S.G. / Lyons, J.M. | Tema Archiv | 1979




    3D Boundary Layer Computations on Wing-Pylon-Nacelle Configurations

    Houdeville, R. / Bardoux, P. / Moreux, V. et al. | British Library Conference Proceedings | 1996