机翼表面结冰数值模拟

Numerical simulation of ice accretion on airfoil

分别采用欧拉-拉格朗日模型和多孔介质模型建立了空气绕流机翼流动、空气夹带过冷水滴运动和机翼表面冰层增长的数理模型,并进行了数值求解.获得空气绕流机翼流场、空气夹带的过冷水滴运动轨迹、机翼表面过冷水滴的收集系数分布、冰层厚度分布和冰层质量增长情况,并分析了攻角和过冷水滴直径等因素的影响.结果表明:水滴收集系数随着攻角和水滴平均直径的增大而增大;冰层覆盖整个机翼的前半部上下表面,以驻点附近最为集中,随时间增长而愈严重;随着功角增大,下表面积冰加重;但当攻角为15°时,总体结冰量却较之低攻角时减小.

Numerical simulation of ice accretion on an airfoil was conducted based on a combined model of Euler-Lagrange method and porous media model. The flow field around the airfoil, the trajectories of super-cooled water droplet, the distribution of local collection efficiency, and the accretion process of ice on the airfoil surface were obtained under different conditions. The significant effects of attack angle and super-cooled droplet diameter on the distribution of impingement region, local collection efficiency, and thickness and mass of ice accretion were found. The results show that the bigger the attack angle and droplet diameter are, the bigger the local collection efficiency is. The ice accrete on the leading edge, especially near the stagnation point. The layer thickness increases with time. The ice layer mass accreted on the lower surface become larger with the increase of attack angle. The ice layer mass for the attack angle 15° is less than that for the smaller attack angle.