三维机翼跨音速颤振的分布式并行计算

Distributed Parallel Method for the Transonic Flutter of Flexible Wings

以多台微机组成分布式计算系统,利用无限插值方法(TFI)生成三维多块贴体运动网格,以Navier Stokes方程为控制方程,求解三维机翼的跨音速非定常气动力,并与颤振方程耦合迭代计算,求解机翼广义位移响应的时间历程,根据广义位移的时间历程的衰减、等幅和发散振荡等情况确定机翼跨音速颤振临界条件.通过算例验证,计算结果与实验结果和理论分析相吻合.

Based on a distributed parallel computing system, a new approach to the transonic flutter of a flexible wing was presented by coupling the computational fluid dynamics (CFD) method with the computational structural dynamics (CSD) method, by using a transfinite interpolation (TFI) scheme to generate a multi-block C-H moving grid, the aerodynamic analysis was carried out by solving the three-dimensional unsteady Navier-Stokes equations. By coupling with the flutter motion equations, the response of the time history of generalized coordinates was found. The critical velocity is got on the base of the response by considerably decreasing the computing time, a multidisciplinary analysis code runs on a distributed parallel computer system by using the PVM library. Computational results are presented for the transonic flutter of wings with deformed shapes as found in flutter simulations.