【摘要】 本文采用数值方法对机翼颤振进行仿真。由于大型机算机和计算流体力学软件日益成熟,流体运动部分可以"如实做来",不必做任何线化假定,所以对物体外形,周围的气流速度无任何限制。这样开发的算法可以广泛用于流体与固体有相互作用的场合,如弹壳分离、副油箱抛投等难题。本文的算例是计算存在流固耦合作用时机翼在高亚音速流及跨音速流中的颤振问题。本方法将机翼的连续系统弹性结构模型与非线性雷诺应力平均N S方程的流体模型弱耦合求解。文中考虑了三维机翼在多个马赫数下的气动响应过程。更多还原

【Abstract】 In this paper, the weak-coupled solid-liquid method is adopted to simulate the vibration of a thin wing. With the development of supercomputers and CFD software, the simulation in computer can be to some extent the same as the real physical phenomena without any linearization suppositions in it. Such method can be applied comprehensively to many situations, such as the separation of a missile and its shells. In our method, the elastic model of the three-dimensional wing is weakly coupled via several pre-computed vibration modes to the Renold equations of the air. To identify the different vibration patterns of wing in transonic flows, the simulations are executed with Mach ranging from 0.6 to 0.8, demonstrating a Mach number limit for divergence existing in the range (0.75, 0.8).更多还原