Based on a real turbine inlet guide vane

the two-dimensional flow field of a turbine cascade was simulated by using the circulation control blade profile with different Coanda surfaces. At the cascade exit being high subsonic and supersonic conditions

the aerodynamic performance and the detailed flow fields of different blade profiles were explored. The mechanism of Coanda effect on turbine cascade was discussed. When Mach number at the cascade exit was 0.60

the jet entrained the mainstream well and the loss reduced. When Mach number at the cascade exit increased to 0.85

the ability of the jet carrying the mainstream was still fine. When the cascade exit was at supersonic flow condition

on the Coanda surface with a small curvature in front

the jet turmed to the center of the flow channel and detached the wall in advance on account of the shock wave. On the Coanda surface with a large curvature in front

the jet adhered to the blade quite well. However

it did not mix with the mainstream for good due to the fillet between the jet exit and the suction surface.