TURBULENT SLOT INJECTION STUDIES AT MACH 6.
NEW YORK UNIV BRONX DEPT OF AERONAUTICS AND ASTRONAUTICS
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The use of film cooling for protecting a surface exposed to high temperature air at hypersonic speeds is investigated experimentally. The purpose of the work is to investigate the effects of injecting a coolant on the surface of a hypersonic vehicle in the turbulent boundary layer, and to try to obtain correlation parameters as well as the effective cooling lengths. The tests were conducted in a Mach 6 contoured axisymmetric nozzle with a streamlined centerbody. The Reynolds number in the test section was in the range of 2-3.6 x 10 to the 6th power per inch. Heat transfer distributions were obtained for various injection mass flow rates and the effect of injection on the velocity, temperature and Mach number profiles was studied. Correlations for the adiabatic wall temperatures with injection rates were obtained. Skin friction coefficients were obtained using Baronti-Libby transformations into the incompressible plane. The measured transient heat transfer rates obtained by the thinskin techniques agree with the values predicted by the flat plate reference enthalpy method for the case of no injection. Author
- Fluid Mechanics