Prediction of 2D Viscous Transonic Flow in Compressor Cascades Using a Semi-Empirical Shock/Boundary-Layer Interaction Method

Abstract

A fast and robust calculation method for turbulent shock boundary-layer interaction is presented which enables the design engineer in quickly estimating the boundary-layer behaviour of a transonic compressor profile section. The separated flow in the vicinity of a shock is described in terms of the boundary-layer properties ahead of the shock and the shock strength itself. The method is incorporated in an integral boundary-layer procedure and coupled with the Euler-equations by the equivalent source concept. Calculations for the flow in transonic and supersonic compressor cascades demonstrate the ability of the present method and show good agreement with boundary-layer properties and Mach number distributions obtained from measurements.