Abstract
The 3D compressible Navier-Stokes equations with Baldwin-Lomax turbulence model are solved to study the flow separa-tion phenomenon in a NASA Transonic Flutter Cascade. The influence of the incidence angle and the inlet Mach num-ber on the flow pattern in the cascade is numerically stud-ied. 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 sub-sonic 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.