Abstract

A simplified icing model combined with Eulerian two-phase flow theory has been proposed and the method was employed for direct simulation of ice accretion occurred on an aircraft wing. An innovative wall boundary condition treatment has been proposed to properly depict the phenonmenon of droplet impact on the wing surface, resulting in enhanced numerical stability in solution process and better agreement with experimental data. The icing model was derived on the basis of the extended Messinger model, and as well as the assumption that the overflow direction follows the air streamline just above the water film. Several concepts like the critical ice thickness have been presented to facilitate the use of this icing model for predicting three-dimensional ice accretions. Preliminary multistep simulation results for one moderate mixed ice accretion case are compared with available experimental data, together with the corresponding single-step results. Further simulation case studies concerning typical glaze ice of more irregular shape and the effect of simulation step interval to update the geometry and the flowfield will be conduted and detailed results will be presented in the final manuscript