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本文使用数值模拟方法研究了活动翼面对翼型背风面分离的控制作用。数值实验的模型为一头部装有一可旋转圆柱的对称Joukowsky翼型。使用的数值方法为在贴体网格上用有限差分法求解可压流的NS方程。数值实验表明,当头部圆柱以一定角速度旋转时,其升力比不旋转时有明显的增加,分离也受到一定程度的控制。
In this paper, numerical control method is used to study the control effect of active wing on airfoil leeward separation. The model of the numerical experiment is a symmetrical Joukowsky airfoil with a rotatable cylinder on its head. The numerical method used was to solve the squeezable NS equation by finite difference method on the body-fitted grid. Numerical experiments show that when the head cylinder rotates at a certain angular velocity, the lift of the head cylinder increases obviously when it rotates without rotation, and the separation is controlled to a certain extent.