An analysis is presented on the compressible inviscid vortex flow over three delta wings with sharp leading edges with leading edge sweep angles phi = 60, 70, and 76 deg using numerical solutions of the Euler equations. Presentations of the results are given for Mach numbers ranging from M infinite = 0.1 to 0.8 and for angles of attack up to the onset of vortex breakdown. The paper focuses the attention on the effects of the vortex flow on the flowfield of a delta wing. The occurence of shock waves of two types, crossflow and terminating (or rear) shocks in the vortical flowfields, are investigated; the possibility of shock-induced vortex breakdown and the effects of compressibility on the rapid performance degradation of delta wings after vortex bursting are studied in detail. It is shown that the onset of the vortex bursting at the wing trailing edge is only weakly influenced by the freestream Mach number. The upstream progression of the vortex bursting, however, is faster for supersonic vortex cores. For transonic flows, terminating shocks are observed downstream of vortex bursting. Crossflow shocks, however, may already develop for low-subsonic freestream Mach numbers. Also, it is found that the core flow is already compressible for freestream Mach numbers M infinite approximate 0.1 and that significant amounts of entropy and circulation are generated within the core.


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    Title :

    Compressible inviscid vortex flow of a sharp edge delta wing


    Additional title:

    Die kompressible reibungsfreie Wirbelströmung über Deltaflügel mit scharfen Flügeleintrittskanten


    Contributors:

    Published in:

    AIAA Journal ; 33 , 4 ; 680-687


    Publication date :

    1995


    Size :

    8 Seiten, 14 Bilder, 25 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English







    The Compressible Inviscid Vortex Flow of a Sharp Edge Delta Wing

    Longo, J. M. A. | British Library Online Contents | 1994


    The Compressible Inviscid Vortex Flow of a Sharp Edge Delta Wing

    Longo, J. M. A. / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1994