Computational fluid dynamics reveals film cooling efficiency in supersonic flow at Mach 2.35, suggesting effects of shock waves.
A computational fluid dynamic study on supersonic film cooling is presented. A coolant gas is injected along a wall with sonic speed tangentially to a primally flow of Mach 2.35. The calculated results such as a wall pressure, a pitot pressure, and an adiabatic wall temperature distributions are compared with experimental data. Film cooling efficiency is also estimated and compared. Effects of impinging shock waves on the film cooling efficiency and the flow structure are also examined using two types of shock wave generators of different shock strength.
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Kimura et al. (1995) studied this question.
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