Abstract: A model for predicting aerodynamic stability of axial compressor in turbojet or turbofan engine is presented.The detailed numerical analyses for three examples for stability operating limits of 9-stage compressor,3-stage fan and 5-stage high-pressure compressor are given.It is shown that the compressor stability operating limit can be precisely predicted when control rule is n f =constant or n h =constant.It is also found that the numerical model and recognition criterion for aerodynamic stability in the axial compressor are feasible.The computed results are in good agreement with the experimental data obtained at medium and high rotating speeds.