本文采用流固耦合的数值方法研究了机翼在0°～50°攻角下的颤振。计算结果表明,随着来流攻角α0的增大,机翼的固有频率对颤振的影响越来越大,颤振由线性的强迫振动逐渐发展成为非线性的自激振动,而当α0增加到一定程度以后,大尺度分离流交替地从机翼头部和尾部产生,机翼和流场会发生共振,引起机翼的失速颤振。 In this paper, the flutter of airfoil at 0 ° ~ 50 ° attack angle is studied by the numerical method of fluid-solid coupling. The calculation results show that with the increase of the angle of attack α0, the natural frequency of the wing has more and more influence on the flutter, and the flutter gradually develops from the linear forced vibration to the nonlinear self-excited vibration. When α0 After increasing to a certain extent, the large scale separation flow is alternately generated from the wing head and the tail, and the wing and the flow field will resonate, causing the wing to fly out of flutter.