The deviation and loss models were developed by taking into account different influential factors using two-dimensional streamline curvature mathematic method at off-design conditions.The internal flow field of NASA(National Aeronautics and Space Administration) Stage 37 was calculated

and then the characteristic curves of design and off-design points were obtained.Through comparison between simulation and experimental values

the results show that the predicted characteristics and parameters distribution of compressor are in good agreement with the experimental values.This method can predict the performance and span-wise aerodynamic parameters of transonic axial compressor with better accuracy and can be used for compressor design and optimization.