抄録
In the super sonic flow through the cascade of a gas-turbine engine, flow separation and shock waves are important phenomena impacting the performance. This report describes an basic experiment to detect these phenomena using hot film sensors. In the super sonic wind tunnel test, flow separation or a shock wave is induced to occur on the surface of the cone-like model at Mach 2.5. Data are collected from hot film sensors located on the surface. Schlieren and oil flow visualization method are also applied to check the flow. As the results, the separation and the shock wave can be detected by the differences between the sensor output.
