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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Shock-induced boundary layer separation in overexpanded conical exhaust nozzles


    Additional title:

    AIAA J


    Contributors:
    Arens, M. (author) / Spiegler, E. (author)

    Published in:

    AIAA Journal ; 1 , n 3


    Publication date :

    1963


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




    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