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飞机机翼结冰过程的数值模拟
引用本文:陈维建,张大林.飞机机翼结冰过程的数值模拟[J].航空动力学报,2005,20(6):1010-1017.
作者姓名:陈维建  张大林
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:提出了一种适用于各种结冰气象条件下飞机机翼结冰过程的数值模拟方法。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,对不同气象条件下飞机机翼的结冰过程进行了数值模拟,得到了4°攻角NACA 0012翼型表面霜状冰、混合冰及瘤状冰3种冰形。所得冰形与文献中的试验数据和计算结果吻合良好,表明本文方法有效。另外还计算了不同的冰形对机翼升、阻力的影响,结果表明瘤状冰对机翼气动特性的影响最大。

关 键 词:航空、航天推进系统  数值模拟  防、除冰  霜状冰  混合冰  瘤状冰
文章编号:1000-8055(2005)06-01010-08
收稿时间:2004/11/29 0:00:00
修稿时间:2004年11月29

Numerical Simulation of Ice Accretion on Airfoils
CHEN Wei-jian and ZHANG Da-lin.Numerical Simulation of Ice Accretion on Airfoils[J].Journal of Aerospace Power,2005,20(6):1010-1017.
Authors:CHEN Wei-jian and ZHANG Da-lin
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
Abstract:A numerical simulation approach is presented to simulate the ice accretion on airfoil which can deal with the ice accretion under various atmospheric conditions.Incorporating the two-phase model of air supercooled droplets in the Eulerian coordinate,this approach was carried out to simulate the ice accretion on the NACA 0012 airfoil under different atmospheric conditions,and the final ice shapes(rime,mixed and glaze ice shapes) were predicted.The comparison between the results of this paper and the experimental data as well as other icing codes indicates that the current approach is applicable and effective.Also the effect of different ice shapes on lift and drag coefficient were assessed.The results indicate that the glaze ice has the most adverse impact on airfoil aerodynamic performance.
Keywords:aerospace propulsion system  numerical simulation  anti/de-icing  rime ice  mixed ice  glaze ice
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