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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。
With the help of the exact solution of unsteady potential flow around a three-dimensional thin wing under the acoustically induced excitation, this paper further analyzes the mechanism of acoustic excitation limited to weak disturbance, and discusses the influence of acoustic source parameters on the flutter boundary , And through the theoretical calculation of acoustic-vortex coupling, the original wind tunnel experiment is explained. The results show that the acoustically induced acoustical loads play different roles in the acoustical loads of different positions. Moreover, there are certain relationships between the parameters of the system during the process of acoustic flutter control, The best parameters must be selected reasonably. The research in this paper provides a theoretical basis for the practical application of acoustic control technology in the field of aerodynamics.