本文以小扰动位势流理论为基础,采用局部线化假设,建立了三维振动机翼的跨音速下洗积分方程;给出了跨-亚音速流核函数的计算方法;用推广的偶极子栅格法计算了矩形谐振动机翼上的非定常压力分布。结果表明,本方法可以较准确地计算非线性的跨-亚音速非定常流动,关于跨-超音速流动的数值解法,尚需作进一步的研究。 In this paper, based on the theory of small perturbation potential flow, the translinear sub-sonic integral equation of the three-dimensional vibrating wing is established by using local linearization assumptions. The calculation method of the cross-subsonic flow kernel function is given. The sub-grid method calculates the unsteady pressure distribution on the rectangular resonant vibration wing. The results show that this method can calculate non-linear cross-subsonic unsteady flow more accurately. For the numerical solution of cross-supersonic flow, further research is needed.