In the numerical simulation process of wing hot air anti-icing, the flow field is solved according to the Navier Stokes equation, and the water droplet impact characteristics are solved by the Euler method, and the solved internal and external flow fields are coupled with heat transfer through the skin heat conduction to achieve stability, and then the simulation of icing is started to carry out the numerical calculation of wing hot air anti-icing and overflow ice formation. The calculation results show that the numerical simulation of hot air anti-icing is feasible and reasonable. In this paper, the numerical simulation method was used to simulate the anti-icing process of wing hot air, and the different ice overflow height and locations caused by insufficient bleeding air temperature or different wing hot air protection area were obtained. The influence of the bleeding air temperature and the anti-icing area on the formation of wing overflow ice was analyzed. The results show that the bleeding air temperature directly and positively affects the skin surface temperature after heat exchange. The lower the bleeding air temperature is, the higher the overflow ice is, and the greater the influence on the lift is. The scope of the hot air protection area will also affect the overflow icing results. The larger the hot air protection area is, the farther the overflow ice is, and the lower the ice height is, the weaker the impact on the lift is.