Measurements in the transition region of a turbine blade profile under compressible conditions

The suction surface of a linear transonic turbine cascade was experimentally investigated. The transition region was measured by utilizing hot film anemometry and the cascade was instrumented with an array of Senflex nickel heated hot film sensors. To determine the boundary layer edge Mach number distribution for the compressible test cases, pressure measurements were obtained in the settling chamber and at a number of locations on the suction surface. The results show that the introduction of correlations to include the effect of Mach number for transition onset, resulted in better agreement with the measurements