The cooling-film behavior in an adiabatic supersonic air main flow over a flat plate is investigated using direct numerical simulations. Air and helium are employed as cooling gases and are injected with a low rate in the wall-normal direction through a single infinite spanwise slit into the laminar or turbulent boundary-layer flow. The blowing is realized by prescribing a fixed distribution of the cooling-gas mass flux, mass fraction, and temperature at either the orifice location without the cooling-gas channel (modeled blowing) or at the lower end of the included blowing channel (simulated/interacting blowing), thus allowing for an interaction of the main and cooling-gas flows. The influence of the modeling, the main-flow boundary-layer state, and the cooling-gas type on the film-cooling effectiveness and the skin-friction alteration is scrutinized; and valuable data for the validation of less costly computational fluid dynamics methods employing turbulence models are gained from this fundamental study.


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    Title :

    Direct Numerical Simulation of Foreign-Gas Film Cooling in Supersonic Boundary-Layer Flow



    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040





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