The improved three-dimensional model called compressor stability analysis code plus (CSAC+) was developed by adding an axisymmetric left characteristic. The steady aerodynamic performances and stall inception characteristics of NASA Rotor 37 under total pressure distortion inlet condition were modeled and analyzed by CSAC+. And compared with NUMECA simulation results

both of the modeling characteristics were fitted well. The relative error of total pressure ratio near stall point for both CSAC+ and NUMECA results was 1.05%. For near stall flow field analysis

it was found that as the flow rate decreased

a low speed or even reverse flow region appeared at the tip of rotor which was located behind the edge of the distortion zone. The region could be considered as the stall inception position under total pressure distortion. The stall inception and the post-stall flow characteristics of the compressor under inlet distortion were also analyzed with CSAC+. At the stall inception

the modal wave turned into part blade height stall after full development. The stall occupied 40% blade height

and the propagation frequency of the stall group was about 60% of the rotor rotation frequency. The stall group showed periodic exfoliation and fusion during propagation.