基于非结构动网格的跨音速颤振研究

Analysis for transonic flutter based on unstructured dynamic grid method

采用流固耦合的方法对跨音速颤振进行了数值模拟。流体方面在改进的非结构动网格的基础上应用中心格式的有限体积法求解了Euler方程。结构方面则在Euler方程的基础上求解了后掠机翼典型剖面的结构方程。用时间推进的方法计算了结构响应特性。最后计算了NACA64A006翼型剖面的跨音速颤振边界,与相关实验结果吻合的比较好。

An efficient fluid-structure interaction solver based on dynamic unstructured grids is developed .The unsteady Euler equations are fully coupled with the flutter equations of a typical Isogai wing section and integrated forward in time.CFD solver is based on an unstructured cell-center finite volume algorithm.Finally transonic flutter boundary prediction for a typical wing section NACA64A006 is present and compared well with experimental result.