Abstract: In this paper, the circumferential average body force model for the transonic axial flow compressor is derived, and numerical computing platform is built based on the commercial software ANSYS CFX. The body force model is added to the ANSYS CFX three-dimensional control equations in form of source terms, and a more efficient and effective compressor inlet distortion numerical calculation method is developed. Then the full flow channel of the NASA Stage 37 transonic single-stage compressor is simulated by using this method, and the compressor performance characteristics and flow field distribution at 70% design speed and uniform intake condition are calculated. The performance characteristics and the flow field distribution of the calculation results agree well with the experimental results, indicating that the method is feasible and correct. Then, the performance and flow fields of the compressor under circumferential intake distortion condition are predicted by this method, and the simulation results show the influences of the inlet distortion on the compressor performance accurately.