Turbulent heat-transfer measurements were made on transpiring flat plate model in Mach 8 tunnel using nitrogen, helium and argon as injection gases; model consisted of impermeable leading edge, transpiration section, and downstream section instrumented with asymptotic calorimeters; reduction in heat flux for transpiring section was obtained at higher blowing rates and Mach numbers than previously reported, whereas downstream heat flux results may be first quantitative measurements of their kind; reduction in turbulent heat flux to transpiring and downstream surfaces is found to be insensitive to Mach and Reynolds number, and transpiration gas.


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    Titel :

    Hypersonic turbulent transpiration cooling including downstream effects


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Woodruff, L.W. (Autor:in) / Lorenz, G.C. (Autor:in)

    Erschienen in:

    AIAA Journal ; 4 , n 6


    Erscheinungsdatum :

    1966


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Transpiration cooling in hypersonic flight

    Tavella, Domingo / Roberts, Leonard | NTRS | 1989


    Transpiration Cooling in Hypersonic Flight

    D. Tavella / L. Roberts | NTIS | 1989



    Transpiration-Cooling Heat Transfer Experiments in Laminar and Turbulent Hypersonic Flows

    Naved, Imran / Hermann, Tobias / Hambidge, Chris et al. | AIAA | 2023