Abstract: Based on Eulerian two-phase flow theory,the rime ice accretions on an aircraft wing in three-dimensional application were numerically simulated.The governing equations for droplets in three-dimensional application were established according to the droplet pseudo-fluid model.A set of numerical methods for solving the droplet governing equations were proposed.The local collection efficiency and impingement area on the wing were computed from the solution of the three-dimensional droplet flowfield.A method of building three-dimensional ice accretion shape was proposed.The rime ice accretions on an ONERA M6 wing under different angles of attack were predicted numerically and the effects of icing conditions on the ice accretion were analyzed.