改进的翼型积冰数值模拟方法

陈科; 曹义华; 潘星

改进的翼型积冰数值模拟方法

北京航空航天大学航空科学与工程学院, 北京 100083

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出版历程
- 收稿日期: 2006-11-15
- 修回日期: 2007-01-17
- 刊出日期: 2007-11-28

An improved numerical simulation method for airfoil ice accretion

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 基于微团概念,以雨滴运动的基本假设出发,对翼型积冰的拉格朗日方法进行了改进.新方法克服了原方法计算效率低、冰形同雨滴分布密度及网格密度相关的缺点,继承了原方法的鲁棒性,不存在欧拉方法的收敛性问题.为验证方法的正确性,计算了NACA0012翼型在0°和4°攻角下的霜冰积冰情况、表面水收集量和局部撞击系数.结果表明新方法减少了计算量,预测的冰形和实验结果一致,并分析了积冰对气动性能的影响.
- 航空、航天推进系统 /
- 积冰 /
- 数值模拟 /
- 撞击极限 /
- 气动性能 /
- 计算流体力学
Abstract: An improved numerical method of simulating ice accretion on airfoil was developed based on parcel concept following the fundamental assumption of droplet movement.This method has overcome the shortages of traditional Lagrangian method,such as:low computation efficiency,ice shape dependence on droplet partition density and grid consistency.But,it has also maintained the robustness of original method,without the issue of convergence in Euler method.NACA0012 rime ice accretion,local droplet collection and local impingement efficiency at 0° and 4° AOA(angle of attack) are simulated with this method in order to verify its correctness.The calculated results show that,this improved method contributes to reduce the calculation efforts.The predicted ice shape was consistent with the experimental result,while the effect on aerodynamics of airfoil was also analyzed.
- aerospace propulsion system /
- icing simulation /
- impingement property /
- air performance /
- computation fluid dynamics(CFD) /

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参考文献(12)

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