Numerical study on flow separation of a transonic cascade

The 3D compressible Navier-Stokes equations with Baldwin-Lomax turbulence model are solved to study the flow separation phenomenon in a NASA Transonic Flutter Cascade. The influence of the incidence angle and the inlet Mach number on the flow pattern in the cascade is numerically studied. When the incoming flow is subsonic, increasing the incidence angle generates a large separation region starting from the leading edge on the suction surface. Higher subsonic inlet Mach number results in a larger separation region. The separation region shrinks and moves downstream when the inlet Mach number is increased to supersonic due to the shock wave boundary layer interaction.