In order to study the influence of icing on aerodynamic characteristics of compressor inlet guide vane, the commercial software FENSAP-ICE was used to calculate the two-dimensional icing of the 50% blade height profile of compressor inlet guide vane. Using the Navier Stokes (N-S) equation, Euler method and Shallow-Water icing model to calculate the flow field, the droplet impact characteristics and the icing shape respectively. The results of NACA0012 airfoil icing calculation and test are compared to verify the reliability of the algorithm. Finally, the two-dimensional glaze ice and rime ice shapes of the blade-profile are obtained, and the flow field changes of the icing-blade-profile are analyzed. The results show that the commercial software FENSAP-ICE can effectively and accurately predict the two typical icing, the glaze ice and rime ice, of the blade-profile; glaze ice will lead to the area of the separation zone at the tail of the blade-profile increased to about 2 times, the separation point on the suction surface of the blade-profile advanced to 1% of the chord length, the speed nonuniformity at the outlet of the blade-profile increased, and the maximum increase of total pressure loss coefficient of blade-profile is 22%. However, the influence of the rime ice on the aerodynamic characteristics of the blade-profile is very small; the decline of the aerodynamic characteristics of the blade-profile is mainly affected by the upper separation vortex in the separation zone, and the lower separation vortex is formed by the mixing of the upper separation vortex and the main stream, which has little influence on the aerodynamic characteristics of the blade-profile.