Numerical investigation of boundary layer suction in an axial transonic compressor cascade

Based on the numerical investigations on the performance of an axial transonic compressor cascade with different suction slot locations and suction mass-flow, it has been shown that for a given inlet Mach number and flow angle, there exist an optimal suction mass-flow corresponding to the suction slot location.And the optimal suction mass-flow increases as the suction slot moves far from the shock location towards the trailing edge.The perfect suction slot location should be at the beginning of the transition region where the boundary layer thickness has developed to a local maximum value downstream of the shock.