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飞机机翼表面霜状冰结冰过程的数值模拟
引用本文:张大林,陈维建.飞机机翼表面霜状冰结冰过程的数值模拟[J].航空动力学报,2004,19(1):137-141.
作者姓名:张大林  陈维建
作者单位:南京航空航天大学,航空宇航学院,江苏,南京,210016
摘    要:提出了一种处理结冰后结冰表面固壁区域移动的移动边界技术,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,对霜状冰的结冰过程进行了数值模拟,得到了NACA0012机翼在0°和4°攻角下机翼表面结冰后形成的冰形,与文献中的实验数据对比,表明本文的方法是可行和有效的。

关 键 词:航空、航天推进系统  数值模拟  防、除冰  边界移动  霜状冰
文章编号:1000-8055(2004)01-0137-05
收稿时间:2003/9/25 0:00:00
修稿时间:2003年9月25日

Numerical Simulation of Rime Ice Accretion Process on Airfoil
ZHANG Da-lin and CHEN Wei-Jian.Numerical Simulation of Rime Ice Accretion Process on Airfoil[J].Journal of Aerospace Power,2004,19(1):137-141.
Authors:ZHANG Da-lin and CHEN Wei-Jian
Institution:Nanjing University of Aeronautics and Astronautics, Nanjing210016, China;Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
Abstract:To simulate the ice accretion on airfoil,a boundary moving technique is proposed to deal with the distortion of airfoil surface due to ice accretion on the leading edge.Incorporating the two-phase model of air-supercooled droplets in the Eulerian coordinates,this technique was applied to simulating the process of the rime ice accretion (the droplets freeze at the instant impinging on the airfoil) on the NACA 0012 airfoil,and the ice profile after ice accretion was achieved successfully.And the brief comparison between the results of this paper and the experiments indicates that the current method is applicable and effective.
Keywords:aerospace propulsion system  numerical simulation  anti/de-icing  boundary moving  rime ice
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