Compressible flows over a 60° sweep delta wing with a sharp leading edge undergoing pitching oscillations are computationally studied. Emphasis in this study is on possible supersonic flow structures and their variations during the pitching motion of a delta wing. Unstructured grid, k-ω SST turbulence model and a dual-time implicit time integration are used. Accurate simulations are performed for various Mach number and angles of attack to cover different flow structures and phenomena associated with them. Variations of flow patterns in a crossflow plane, pressure coefficient on the wing surface, and hysteresis loops associated with vortex core location during a pitching cycle are investigated. The trends with Mach number, mean angle of attack, amplitude of pitching and pitching frequency are illustrated.


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    Titel :

    Computational investigation of the flow structure over a pitching delta wing at supersonic speeds




    Erscheinungsdatum :

    2016



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik
    Lokalklassifikation TIB:    275/7040



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    Vortex Breakdown over a Pitching Delta Wing

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    The pitching delta wing

    Gad-el-Hak, M. / Ho, C.M. | Tema Archiv | 1985


    Vortex Breakdown Over a Pitching Delta Wing

    Gursel, I. / Yang, H. / AIAA | British Library Conference Proceedings | 1994