Flow in overexpanded supersonic nozzles reviewed; although 5 flow regimes can be discerned, depending on nozzle pressure ratio, regime of most interest is one characterized by oblique shock patterns in nozzle and flow separation from nozzle wall; pressure rise associated with separation correlates well with Mach number at separation point; formulation for pressure rise required to separate flow provides excellent agreement with experimental data over wide range of operating conditions and prediction of nozzle performance.


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    Titel :

    Shock-induced boundary layer separation in overexpanded conical exhaust nozzles


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Arens, M. (Autor:in) / Spiegler, E. (Autor:in)

    Erschienen in:

    AIAA Journal ; 1 , n 3


    Erscheinungsdatum :

    1963


    Format / Umfang :

    4 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Separation Instabilities in Overexpanded Nozzles

    Welle, Richard / Hardy, Brian / Murdock, John et al. | AIAA | 2003


    SEPARATION INSTABILITIES IN OVEREXPANDED NOZZLES

    Welle, R. P. / Hardy, B. S. / Murdock, J. W. et al. | British Library Conference Proceedings | 2003