A brief survey is given on the study of transonic shock/boundary layer effects in flight. Then the possibility of alleviating the adverse shock effects through passive shock control is discussed. A Swedish flight experiment on a swept wing attack aircraft is used to demonstrate how it is possible to reduce the extent of separated flow and increase the drag-rise Mach number significantly using a moderate amount of perforation of the surface.


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    Titel :

    Shock-Boundary-Layer Interaction in Flight


    Beteiligte:
    A. Bertelrud (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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