Numerical method to simulate rime ice accretions on an airfoil
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摘要: 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NACA 0012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.Abstract: 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.
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Key words:
- ice accretion /
- two-phase flows /
- permeable wall /
- collection efficiency /
- numerical simulation
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