A numerical simulation method was built based on the conception of fluid-solid coupled heat transfer

and ice prediction under hot air anti-icing system was carried out in associated with ice accretion thermodynamics model. Both the internal and external flow fields were got by solving N-S equation using cell-centered finite volume method. The droplet impingement result was calculated by Euler method based on the external flow field. Three-dimensional heat transfer partial differential equation was solved to get the heat transfer characteristic of the thin-gauge skin. Heat transfer from internal flow to external flow field was accomplished by using interface interpolation method. Three-dimensional ice accretion thermodynamics model was built with which ice ridge was predicted. The result shows that the heated wing surface temperature can get as high as 308 K

and ice ridge is accreted on both the upper and lower surfaces just after the heated zone when the hot air anti-icing system is on. Then

by analyzing the result

it proves that the method is rational and effective.