Based on the Eulerian two-phase flow theory, a numerical method to simulate rime ice accretions on an airfoil has been developed. The semi-implicit method for pressure linked equations (SIMPLE) algorithm on a collocated grid was employed to solve the governing equations for the airflow. In order to simulate droplets impinging on an airfoil, a permeable wall was proposed to solve the governing equations for supercooled droplets. The collection efficiency and impingement limits were obtained from the droplets- flowfield. The process of ice accretion was simulated using the assumption that ice accumulates layer-by-layer and the ice shape was built with the assumption that ice grows in the direction normal to the airfoil surface. The rime ice accretions on a NACA 0012 airfoil at 0° and 40° angles of attack have been investigated and there is agreement between the simulated results and experimental data. A conclusion that ice accretions degrade the airfoil-s aerodynamic performance can be drawn based on the analysis of pressure distribution along the iced airfoil.