The linear stability of fully three-dimensional supersonic boundary layers formed over swept-wing configurations is investigated using a modified version of the linear stability code COSAL. Configurations studied include a highly swept leading-edge model to be utilized for transition studies in the LARC Low-disturbance Mach 3.5 Pilot Tunnel. The model is a representation of the leading edge of a laminar flow control wing for the F-16XL aircraft. In addition, the region over a laminar flow control glove fitted on the mid-portion of an F-16XL wing was studied. For each configuration, estimates of the location of the onset of transition were computed using linear stability theory and the eN method. The effectiveness of suction in stabilizing the boundary layer over the F-16XL wing glove was also investigated.


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    Titel :

    Application of Linear Stability Theory in Laminar Flow Design


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Spall, Robert (Autor:in) / Iyer, Venkit (Autor:in)

    Kongress:

    Aerospace Technology Conference and Exposition ; 1991



    Erscheinungsdatum :

    01.09.1991




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Application of linear stability theory in laminar flow design

    Iyer, V. / Spall, R. | Tema Archiv | 1991


    Stability Theory for Laminar Flow Control Design

    Bushnell, Dennis M. / Hefner, Jerry N. | AIAA | 1990


    Application of stability theory to laminar flow control

    HEFNER, J. / BUSHNELL, D. | AIAA | 1979