| 瘤状冰结冰过程的数值模拟 |
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| 引用本文： | 陈维建,张大林.瘤状冰结冰过程的数值模拟[J].航空动力学报,2005,20(3):472-476. |
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| 作者姓名： | 陈维建 张大林 |
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| 作者单位： | 南京航空航天大学,航空宇航学院,江苏,南京,210016 |
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| 摘 要： | 提出了一种可考虑粗糙度影响的瘤状冰结冰过程数值模拟方法。结合欧拉坐标系下空气-过冷水滴两相流动控制方程的计算,对飞机机翼在不同温度下的瘤状冰结冰过程进行了数值模拟,得到了NACA0012翼型4°攻角下结冰表面的瘤状冰冰形。通过与实验数据对比,表明该的方法是有效的。
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| 关 键 词： | 航空、航天推进系统 数值模拟 防、除冰 瘤状冰 |
| 文章编号： | 1000-8055(2005)03-0472-05 |
| 收稿时间： | 2004/5/12 0:00:00 |
| 修稿时间： | 2004年5月12日 |
Numerical Simulation of Glaze Ice Accretion Process |
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| CHEN Wei-jian and ZHANG Da-lin.Numerical Simulation of Glaze Ice Accretion Process[J].Journal of Aerospace Power,2005,20(3):472-476. |
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| Authors: | CHEN Wei-jian and ZHANG Da-lin |
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| Institution: | College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing210016,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing210016,China |
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| Abstract: | A numerical simulation approach taking the wall roughness effect into account was presented to simulate the glaze ice accretion.Incorporating the biphase model of air and supercooled water droplets in the Eulerian coordinate,this approach has been carried out to simulate the glaze ice accretion on the NACA0012 airfoil.The final ice shape at different temperature was obtained.The comparison with the experimental data indicates that the current approach is applicable and effective. |
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| Keywords: | aerospace propulsion system numerical simulation anti/de-icing glaze ice |
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