Numerical simulation of aircraft hot air anti-icing system and ice ridge prediction

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.