Numerical Simulation Icing On Airfoils And The Effect Of Its Flight Safety

During the flight, due to the impact of supercooled water droplets, the plane windward surface appears icing phenomenon, which is known as the aircraft icing. Once the ice accretion appears on the wings, to change its aerodynamic shape, leading to the lift coefficient decreases, and the drag coefficient increases, lift-to-drag ratio decreases, etc. That causes flight accident.In this paper, the wing icing is researched using numerical simulation, taking NACA0012 airfoil and ONERA-M6 wing as example, research was mainly developed from the following several aspects: Given its viscosity and uncompressibility, the Navier-Stokes equation was chosen to calculate the air flow field; the S-A turbulence model was chosen in order to simulate the separation flow accurately. The motion and impact characteristics of the supercooled water droplets were researched. The supercooled water droplets motion equation were established by the Eulerian two-phase flow method. Comprehensively analysis the influence of the collection coefficient and the influence of the water droplets diameter on the impact characteristic, the collision limit of Langumir-D was greater than the collision limit of Mono-Dispersed. So choosing the Langumir-D distribution was more reasonable to analyze the impact characteristic. The shallow water flow model of water film flow was chosen, the icing shape were gotten by simulating. The results conformed to the characteristics of icing shape, its trend was consistent with relevant literature, so this verified the feasibility of the model.