Boundary-layer shape measurements at the engine inlet on four different hypersonic aircraft forebody designs (with no engine on the forebody) are reported. The measurements provide a qualitative assessment of the effectiveness of various forebody geometries as engine inlet precompression surfaces. The designs, tested in a hypersonic tunnel at Mach 6 and a nominal freestream Reynolds number of 30,500,000, included a semiconical forebody, a configuration similar to a slab delta wing, a conical nose blended into a flat surface, and a conical, complex forebody shape. Boundary layer height as a function of forebody compression is shown for each design.


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    Titel :

    Inlet boundary-layer shapes on four aircraft forebodies at Mach 6


    Beteiligte:
    Lawing, P. L. (Autor:in) / Johnson, C. B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1978-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Inlet Boundary-Layer Shapes on Four Aircraft Forebodies at Mach 6

    Pierce L. Lawing / Charles B. Johnson | AIAA | 1978


    Flow characteristics about concave conic forebodies at high Mach number

    ABBETT, M. / COOPER, L. / DAHM, T. et al. | AIAA | 1975


    The impact of LO-configured forebodies on inlet approach flowfields

    HADDAD, RAYMOND / BINGAMAN, DONALD / SURBER, LEWIS et al. | AIAA | 1991


    The impact of LO-configured forebodies on inlet approach flowfields

    Haddad, Raymond C. / Bingaman, Donald C. / Surber, Lewis E. et al. | NTRS | 1991