Abstract: Using a given velocity profile in boundary layer and the semi-empirical formulas, the integral method to predict boundary layer with adverse pressure gradient caused by shock wave was developed in this paper. The flow field with shock wave in the transonic compressor cascade can be predicted by using of viscous-inviscid iteration procedure. The comparison between the experimental data and the results obtained by means of present method shows that the viscous-inviscid iteration method gives more resonable results than that of inviscid computation.

Key words: cascade, compressors, transonic