机翼颤振的有源声控制

借助于己推导出的声激励下绕三维薄翼的非定常位势流的精确解，本文进一步分析了限于弱扰动的声激励消除颤振的机理，讨论了声源参数对颤振边界的影响，并通过声一涡耦合的理论计算，解释了原有的风洞实验。结果表明，对于不同位置的声源，声致气动载荷的无环量和有环量部分起着不同的作用，而且，在声控制颤振的过程中，系统的各种参数存在一定的关系，必须合理地选取最佳参数。本文的研究为声控制技术在气动领域中的实际应用提供了理论基础。

Active acoustic control of airfoil flutter

Using the derived exact solution to the acoustically induced unsteady potential flow of atwo--dimensional thin airfoil, the mechanism of flutter suppression by active acoustic excitation, knownas an extremely weak flow perturbation, is analyzed further. The parametric effect of sound source on theflutter boundary is discussed, and through the theoretical calculation of the coupled acoustic-vortex, theconducted wind-tunnel experiment is explained. The results show that the noncirculatory and circulatoryparts of the acoustically induced aerodynamic loads play different roles, as the sound source is locatedin different position. Moreover, in the acoustic flutter suppression processl there are certain relationsbetween the parameters of the closed-loop system, and the optimal parameter must be correctly chosen.The present investigation provides a theoretical foundation for the active acoustic control techniquesapplied in the aerodynamic areas