A stability analysis is presented for a vortex pair over a highly swept flat-plate delta wing, by use of a formulation based on the slender-body theory for an inviscid incompressible flow. The vortex pair is found to be truly stable to all disturbances of small amplitude. The stabilizing mechanism has been identified to be the freestream velocity component that tends to pull the vortex pair toward the midplane of the delta wing. Such a mechanism is three dimensional in nature and cannot be provided by a two-dimensional stabilizing device. This result, together with a deduction that the strength of the vortex pair that can be trapped above a delta wing decreases with increasing sweepback angle, generally agrees with laboratory observations.


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    Title :

    Stability of leading-edge vortex pair on a slender delta wing


    Additional title:

    Stabilität des Flügeleintrittskanten-Wirbelpaars an einem schlanken Deltaflügel


    Contributors:
    Huang, M.K. (author) / Chow, C.Y. (author)

    Published in:

    AIAA Journal ; 34 , 6 ; 1182-1187


    Publication date :

    1996


    Size :

    6 Seiten, 7 Bilder, 17 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Stability of leading-edge vortex pair on a slender delta wing

    Huang, Ming-Ke / Chow, Chuen-Yen | AIAA | 1996



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