Abstract: A numerical method for simulating the ice accretion process on airfoil is presented. The inviscid outer flow around the airfoil is solved using a finite volume upwind splitting VanLeer scheme on unstructured grids with distributed parallel computation, and the time integration is a 5stage RungeKutta method. Then it is coupled with the icing model, with a fourthorder RungeKutta scheme for the description of the trajectories of supercold droplets. A simple method is introduced to calculate the icing quantity on the body surface. And the dynamic mesh technique is implemented to adjust the grids for the iced airfoil. This method can describe the icing process almost without any artificial control parameters. After the validation and verification of the numerical method by the ice accretion problem of the NACA0012 airfoil, it is used to simulate the airfoil ice shape of an airplane under icing weather conditions. The numerical results are obtained and compared well with the limited references.

Key words: ice accretion, unstructured mesh, upwind scheme, dynamic grid, numerical simulation