Mach Number Effects on Secondary Flow Development Downstream of a Turbine Cascade

The results of an investigation of the three-dimensional flow downstream of a transonic turbine cascade are presented. The investigation was carried out for a wide range of Mach numbers, extending from M 2is =0.2 up to 1.55. Measurements were made in five planes at different axial locations downstream of the trailling edge by using a miniaturized five-hole probe especially designed for transonic flows