Tip clearance flow and the unsteady flow phenomena of tip leakage vortex have great effect to the stall inception of axial-flow compressor.In this paper

3-Dsteady

unsteady numerical simulation of the transonic axial-flow compressor-NASArotor 37 was investigated.Compared to the numerical results and the experimental test case at peak-efficiency and near stall condition

the numerical results agreed well with experimental test data for estimation of the global performance.For the unsteady computation

Detail analyses of the flow field of the NASArotor 37 led to some preliminary conclusion: the tip leakage flow behave obviously unsteady flow phenomena.Shock-vortex induced the periodic breakdown of the tip leakage vortex.