Experimental and numerical study of supersonic film cooling

An experimental study has been performed at ONERA to simulate film cooling in a rocket engine. Two injector heights and cold and ambient temperature films, as sell as matched and under-and overexpanded films, have been investigated. The mixing process has been documented bg measuring the Mach number and temperature profiles, In addition, wall pressure and temperature, as well as heat transfer coefficients, have been measured. A boundary-layer code has been used to compute this how To achieve a fair prediction of the flow, several turbulence models, including compressibility corrections, have been tested. The prediction of the mixing-layer expansion is crucial for the quality of the computational results, We have concluded that the algebraic models tested are not suitable to compute this how and that the best agreement is achieved with the model of So et al. (So, R. M. C., Zhang, H. S., and Speziale, C. G., "Near-Wall Modeling of the Dissipation-Rate Equation," AIAA Paper 92-0441, Jan. 1992).