A 'pylon vortex generator' concept has been proposed for alleviating the subsonic pitch-up instability of highly swept supersonic-cruise wings. Fixed at a part-span location, this leading-edge device utilizes the lateral velocity component in the flow approaching the swept leading edge to generate a streamwise vortex, opposite in sense to the tip vortex. The vortex-induced downwash outboard of the device serves to control the leading-edge stall development in the wing-tip regions. Wind-tunnel results on 60-deg and 74-deg flat-plate delta wings are presented to illustrate the operation of the pylon vortex generator in modifying the spanwise leading-edge separation characteristics resulting in effective alleviation of the pitch-up.


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    Titel :

    Alleviation of the subsonic pitch-up of delta wings


    Beteiligte:
    Rao, D. M. (Autor:in) / Johnson, T. D., Jr. (Autor:in)

    Kongress:

    Aerospace Sciences Meeting ; 1982 ; Orlando, FL


    Erscheinungsdatum :

    01.01.1982


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Alleviation of the subsonic pitch-up of delta wings

    RAO, D. M. / JOHNSON, T. D. | AIAA | 1983


    Alleviation of the subsonic pitch-up of delta wings

    RAO, D. / JOHNSON, JR., T. | AIAA | 1982


    Subsonic pitch-up alleviation on a 74 deg delta wing

    Rao, D. M. / Johnson, T. D., Jr. | NTRS | 1981



    Subsonic wing rock of slender delta wings

    KONSTADINOPOULOS, P. / MOOK, D. T. / NAYFEH, A. H. | AIAA | 1985