A numerical study of shock wave/boundary layer interaction in a supersoniccompressor cascade

A numerical analysis of shock wave/boundary layer interaction in transonic/ supersonic axial flow compressor cascade has been performed by using a char acteristic upwind Navier-Stokes method with various turbulence models. Two equation turbulence models were applied to transonic/supersonic flows over a NACA 0012 airfoil. The results are superion to those from an algebraic tu rbulence model. High order TVD schemes predicted shock wave/boundary layer interactions reasonably well. However, the prediction of SWBLI depends more on turbulence models than high order schemes. In a supersonic axial flow c ascade at M = 1.59 and exit/inlet static pressure ratio of 2.21, k-(omega) and Shear Stress Transport (SST) models were numerically stables. However, the k-(omega) model predicted thicker shock waves in the flow passage. Loss es due to shock/shock and shock/boundary layer interactions in transonic/su personic compressor flowfields can be higher losses than viscous losses due to flow separation and viscous dissipation.