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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    Titel :

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


    Weitere Titelangaben:

    Stabilität des Flügeleintrittskanten-Wirbelpaars an einem schlanken Deltaflügel


    Beteiligte:
    Huang, M.K. (Autor:in) / Chow, C.Y. (Autor:in)

    Erschienen in:

    AIAA Journal ; 34 , 6 ; 1182-1187


    Erscheinungsdatum :

    1996


    Format / Umfang :

    6 Seiten, 7 Bilder, 17 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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

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


    Leading-edge vortex dynamics on a slender oscillating wing

    JUN, YOUNG-WHOON / NELSON, ROBERT C. | AIAA | 1988


    Leading-edge vortex dynamics on a slender oscillating wing

    Jun, Young-Whoon / Nelson, Robert C. | NTRS | 1988