Shock-induced flow separation takes place in rocket nozzles when operate under over-expanded conditions. Numerical prediction of these supersonic separated flows has been a challenge for the existing RANS models and their respective LES/RANS techniques. In the present research work an extensive and comparative study of these turbulence modelling methodologies has been undertaken to investigate free shock separation flow configuration in thrust optimized contour (TOC) nozzle.


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    Title :

    Turbulence Modelling for Supersonic Separated Flows


    Contributors:
    Shams, A. (author) / Comte, P. (author)


    Publication date :

    2010


    Size :

    12 Seiten





    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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    Siclari, M.J. | Tema Archive | 1992