The phenomenon of separated flow on a series of circular-arc afterbodies was investigated using the Langley 16-foot transonic tunnel at free-stream Mach numbers from 0.40 to 0.95 at 0 deg angle of attack. Both high-pressure air and solid circular cylinders with a diameter equal to the nozzle exit diameter were used to simulate jet exhausts. A detailed data base of boundary layer separation locations was obtained using oil-flow techniques. The results indicate that boundary layer separation is most extensive on steep boattails at high Mach numbers.


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    Titel :

    Boundary layer separation on isolated boattail nozzles


    Beteiligte:

    Erscheinungsdatum :

    08.05.1977


    Medientyp :

    Hochschulschrift


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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    Boundary layer thickness effect on boattail drag

    BLAHA, B. / CHAMBERLIN, R. / BOBER, L. | AIAA | 1976