A concept for nozzle design which incorporates slow expansion rates and a radial flow region is developed for use on a hypersonic (Mach 6) nozzle. It is shown that the boundary-layer suction slot upstream of the nozzle throat is necessary to remove upstream turbulent boundary layers and to initialize a new laminar boundary layer on the downstream nozzle wall. In effect, the laminar boundary-layer flow can be extended more effectively farther downstream by a slow expansion contour based on the present design concept than by a rapid expansion contour used in previous pilot quiet nozzles.


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    Titel :

    Goertler instability and hypersonic quiet nozzle design


    Beteiligte:

    Erscheinungsdatum :

    01.06.1991


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Goertler instability and hypersonic quiet nozzle design

    Chen, Fang-Jenq / Wilkinson, Stephen P. / Beckwith, Ivan E. | NTRS | 1993


    Goertler instability and hypersonic quiet nozzle design

    CHEN, FANG-JENQ / WILKINSON, STEPHEN P. / BECKWITH, AN E. | AIAA | 1993


    Goertler instability and hypersonic quiet nozzle design

    CHEN, FANG-JENQ / WILKINSON, STEPHEN / BECKWITH, IVAN | AIAA | 1991


    Secondary Goertler instability in hypersonic boundary layers

    Whang, Chong / Zhong, Xiaolin | AIAA | 2001