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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    Title :

    Hypersonic turbulent transpiration cooling including downstream effects


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 4 , n 6


    Publication date :

    1966


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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