Transonic flow field around a fighter wing/pylon configuration was simulated by using an implicit upwinding Navier-Stokes flow solver (F3D) and overset grid technology (Chimera). Flow separation and local shocks near the wing/pylon junction were observed in flight and predicted by numerical calculations. A new pylon/fairing shape was proposed to improve the flow quality. Based on numerical results, the size of separation area is significantly reduced and the onset of separation is delayed farther downstream. A smoother pressure gradient is also obtained near the junction area. This paper demonstrates that computational fluid dynamics (CFD) methodology can be used as a practical tool for aircraft design.


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    Titel :

    Juncture flow improvement for wing/pylon configurations by using CFD methodology


    Beteiligte:
    Gea, Lie-Mine (Autor:in) / Chyu, Wei J. (Autor:in) / Stortz, Michael W. (Autor:in) / Chow, Chuen-Yen (Autor:in)

    Kongress:

    AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States


    Erscheinungsdatum :

    01.01.1993


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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

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


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