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 well as matched and under- and overexpanded films, have heen investigated. The mixing process has been documented by 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 flow. 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