Abstract
In the super sonic flow through the cascade of a gas-turbine engine, flow separation and shock waves are important phenomena impacting the performance. In previous report1) flow separation can be detected using hot film sensors. And we show the possibility that shock waves can be detected using these sensors. This report describe additional experiment to improve the detection of shock waves. In super sonic wind tunnel test, two kinds of shock waves, that are differed in strength, are indused to occur on the surface of the cone-like models at Mach 2.5. Data are collected from hot film sensors located on the surface. Schlieren flow visualization method is also applied to check the flow. As the results, the shock wave can be detected by the differences between the sensor output.
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