采用欧拉两相流法对翼型表面霜冰的数值模拟

Numerical method to simulate rime ice accretions on an airfoil

基于欧拉两相流理论提出一种翼型表面霜冰的数值模拟方法.采用同位网格上的SIMPLE(Semi-Implicit Method for Pressure Linked Equations)算法求解空气控制方程;提出一种可穿透型壁面边界模拟水滴对翼型表面的撞击,通过求解过冷水滴的控制方程得到翼型表面的水滴收集特性;利用冰层时间推进法模拟积冰过程,使用积冰法向生长假设生成积冰外形.对NACA0012翼型在0°和4°迎角下的积冰情况进行了研究,冰形预测结果与实验结果一致.通过对结冰翼面的压力分布进行分析,表明积冰对翼型气动性能会产生不利影响.

Based on the Eulerian two-phase flow theory, a numerieal 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 eolleetion 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 eonelusion that ice aceretions degrade the airfoil＇s aerodynamic performanee can be drawn based on the analysis of pressure distribution along the iced airfoil.