Abstract
*† In this work a numerical and experimental investigation of the basic behavior of film cooling at hypersonic flow conditions is presented. For the experiments a ramp model with a transverse blowing slot in respect to the incoming flow is employed. Thereby the thermal loads are measured with thermocouples and an infrared camera. Additionally Schlieren pictures and pressure measurements were made. The experimental results are compared to numerical calculations and both show a high effectiveness of the film cooling technique at hypersonic flow conditions. Furthermore velocity and temperature profiles show the effect of the cooling gas injection to the boundary layer. Finally an estimation is made for cooling a body under real flight conditions.
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