中文摘要：

对30P30N三段翼型失速攻角附近的分离流动进行了数值模拟研究。为了抑制大攻角时背风区的流动分离,在主翼段上表面引入了行波壁变形模型和抛物型局部主动振动模型,利用作者以往发展的动态混合网格技术和相应的非定常计算方法,对变形过程中的非定常分离流动进行了数值模拟,分析了各种变形参数对流动分离的影响。计算结果表明,在适当的条件下,局部主动变形能够抑制翼型背风区的分离,由此可以起到增升减阻的作用,改善翼型的气动性能。

英文摘要：

The subsonic turbulence flow over 30P30N three-element airfoil is simulated numerically at high angle of attack.In order to control the flow separation in the leeward in the cases of high angle of attack,a traveling wave model and an active oscillating model are added to the upper surface of the airfoil.Then the unsteady flows over the morphing airfoil are simulated with an unsteady flow solver based on dynamic hybrid grids,which was developed in previous work.The numerical results show that,in some cases,the flow separation in the leeward will be depressed and even completely eliminated so that the lift coefficient can be increased and the drag coefficient can be cut down to improve the aerodynamic performance of the airfoil at high angle of attack.