风力机叶片翼型结冰的气动性能数值模拟

摘要

In this paper,the Fluent is used to simulate the effect of iced leading edge of the NACA 63418 airfoil on its aerodynamic performance, at attack angle from 0 °to 90 °. The aerodynamic performance of iced leading edge is compared with that of clear leading edge. The results show that: icing has a significant impact on the airfoil aerodynamic performance, and makes stall occurred earlier when the attack angle is ranging from 0 °to 25 °. When the angle of attack is greater than 25 °, icing makes the airfoil drag coefficient increased significantly, and the lift coefficient also has an obvious process of increase , that reaches a maximum at about 50 °and then begins to decline.%采用Fluent软件模拟分析了攻角为0～90°时,结冰对NACA 63418翼型气动性能的影响,并与结冰前翼型的气动性能进行对比.结果表明,结冰对翼型的气动性能有明显的影响,当攻角为0～25°时,结冰使翼型的失速提前发生;当攻角大于25°时,结冰使翼型的阻力系数明显增大,升力系数也有一个明显的上升过程,并在50 °攻角附近达到最大值后开始下降.