Hypersonic flowfield over highly swept delta wings with various types of separation is investigated; heat-transfer rates, pressure distributions, and flow-visualization techniques were used to examine flow over large angle-of-attack range; where boundary-layer type differs across span prior to separation, complex and unusual flow phenomena develop; separated flow is found to form coiled vortices in manner similar to that found at subsonic speeds but with several significant differences. (27745)


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    Titel :

    Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6


    Weitere Titelangaben:

    AIAA J


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 6 , n 12


    Erscheinungsdatum :

    1968


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :