RANS Prediction of Transonic Compressive Rotor Performance Near Stall

Abstract

A series of test cases have been studied to draw conclusions on the numerical prediction of boundary layer development under adverse pressure gradient, including strong shockwave / boundary layer interaction phenomena that influence the performance of a transonic compressive rotor. A density based RANS technique has been selected, employing the Spalart-Allmaras turbulence model. The study concentrates on the predicted effect of endwall boundary layer development and its interaction with the passage shock system. Particular attention is given to predicting the near-stall condition.