The problem of supersonic flow control using fillets and sweep for a wing-body junction has been investigated numerically using a three-dimensional Navier-Stokes code, which employs the MacCormack's time-split finite volume technique. An elliptic grid generation technique with direct control over spacing has been developed for constructing the grid at a filleted wing-body junction. The computed results for pressure distribution, particle paths, and limiting streamlines on the flat plate and fin surface for a swept fin show a decrease in the peak pressure on the fin leading edge and in the extent of the separated flow region. Moreover, the results for filleted juncture clearly show that the flow streamline patterns lose much of their vortical character with proper filleting. It has been demonstrated that fillets with a radius of three-and-one-half times the fin leading-edge diameter are required to weaken the vorticity in the horseshoe vortex by a factor of three for the Mach number and Reynolds number considered in the present study.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Study of supersonic intersection flowfield at modified wing-body junctions


    Beteiligte:
    Lakshmanan, B. (Autor:in) / Tiwari, S. N. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.05.1993



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Study of supersonic intersection flowfield at modified wing-body junctions

    Lakshmanan, B. / Tiwari, S.N. | Tema Archiv | 1993



    Mach Number Effect on Flowfield Over a Delta Wing in Supersonic Region

    Oyama, Akira / Ito, Masato / Imai, Genta et al. | AIAA | 2008


    Controlling Flow in Supersonic Wing/Body Junctions by Passive Means

    Blank, S. C. / Japan Society for Aeronautical and Space Sciences | British Library Conference Proceedings | 1995