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。
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第6期1010-1017,共8页
Journal of Aerospace Power
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
aerospace propulsion system
numerical simulation
anti/de-icing
rime ice
mixed ice
glaze ice
