Film-cooling performance in supersonic flows: effect of shock impingement
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The impact of shock waves on supersonic cooling films is studied using large-eddy simulations (LES). A laminar cooling film is injected through a slot at a Mach number Mai = 1.8 into a fully turbulent boundary layer at a freestream Mach number Ma∞ = 2.44. The cooling film is disturbed by oblique shock waves at deflection angles of 5° and 8° at two downstream positions of the slot. At shock impi...
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ژورنال
عنوان ژورنال: Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
سال: 2013
ISSN: 0957-6509,2041-2967
DOI: 10.1177/0957650912474444