Abstract: Some improvements in previous computation models of blade stall flutter in axial-flow compressors have been made on both aerodynamics and structural dynamics so as to make the models more practical.The calculations show that the effect of in-passage shock and separation flow on the aeroelastic stability of a blading system vibrating in a pure bending mode with single degree of freedom is qualitatively different from that in a predominant bending mode with two degrees of freedom.The coupling of bending and torsion degrees of freedom is probably one of the most important factors which cause onset of the stall flutter .Finally, the stall flutter boundary is preliminarily predicted for an actual rotor and the results are compared with the corresponding experimental data.