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Film-cooling is an active cooling technique that is widely used in conventional gas turbine and rocket engines to manage heat transfer between hot reacting gases and cooler structural components. It is also a candidate technology for the thermal protection of scramjet engines, in which combustion occurs under highly compressible conditions. This paper extends semi-empirical modeling ideas for incompressible wall-jet slot film-cooling to account for both convective and thermal compressibility effects. The new model shows that the influence of compressibility is determined by the magnitude of the average convective Mach number M c , the total temperature ratio θ 0 = T 0s /T 0∞ , and the flow Mach number M HS of the highest-speed stream in the film-cooling flow. In general, increasing M c and decreasing θ 0 improves film-cooling performance. These predictions are validated via comparison with experimental data in three compressible flow regimes: weakly compressible (M c , M HS ≤ 0.3 and 0.6 ≤ θ 0 ≤ 1), moderately compressible (0.3 1.0, and θ 0 < 0.3). The model also resolves disagreements in the literature over the importance of compressibility in film-cooling problems by showing that compressibility effects can be significant, provided the convective and flow Mach numbers are high enough and the total temperature ratio is low enough.
Dellimore et al. (Thu,) studied this question.
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