A three-dimensional, Laminar boundary-layer method is applied to the incompressible flow over a slender delta wing at incidence. The predictor-corrector finite-difference scheme of Matsuno is used to difference the governing equations. The method has the advantages that no iterations are required to advance the solution and the cross-flow derivatives are formed independent of the cross-flow direction. The difference scheme is demonstrated to yield accurate numerical results when compared to the exact solution of the three-dimensional boundary-layer equations for parabolic flow over a moving flat plate. The method is applied to delta wings of various sweep angles at angles of attack up to 20 deg., with the inviscid solution determined using a higher-order, three-dimensional panel method.


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    Titel :

    A Three-Dimensional Boundary-Layer Method for Flow over Delta Wings with Leading-Edge Separation


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    Aerospace Technology Conference and Exposition ; 1985



    Erscheinungsdatum :

    1985-10-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Three-Dimensional Flow over Wings with Leading-Edge Vortex Separation

    F. T. Johnson / E. N. Tinocot / P. Lu et al. | AIAA | 1980


    Three-dimensional flow over wings with leading-edge vortex separation

    Johnson, F.T. / Tinoco, E.N. / Lu, P. et al. | Tema Archiv | 1980


    On Slender Delta Wings with Leading-edge Separation

    Brown, Clinton E / Michael, William H , Jr | NTRS | 1955


    On slender Delta wings with leading-edge separation

    Brown, C.E. / Michael, Jr., W.H. | Engineering Index Backfile | 1955