用改进非结构动网格方法模拟跨音速非定常绕流  

Simulation of Transonic Unsteady Flow with Improved Unstructured Dynamic Grid Method

作　　者：王军利[1] 周洲[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《空军工程大学学报（自然科学版）》2009年第3期10-14,共5页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国防预研基金资助项目(9140A25010106HK03)

摘　　要：对用于非结构动网格生成的弹簧近似方法进行了研究。通过采用顶点弹簧方法,分析研究了弹簧倔强系数的取值,同时通过引入防扭转、防挤压倔强系数和边界修正,对标准弹簧近似方法进行了改进。改进后的方法可以大大提高网格变形能力和网格质量。应用本文发展的非结构动网格生成方法并通过耦合求解基于ALE(Arbitrary Lagrangian-Eulerian)描述的Euler方程,模拟了做谐和振动的矩形刚性机翼及大展弦比后掠机翼弯扭耦合振动跨音速非定常绕流,计算结果与参考文献提供的结果及实验结果吻合良好。In this paper, spring analogy method for dynamic unstructured grids is studied. The stiffness of the springs in the modified vertex spring analogy is analyzed. The standard method is improved in consideration of preventing extrusion, torsion stiffness coefficient and the boundary effect. Applications of the improved spring analogy method to 3D -grids generation show that the new method greatly upgrades the deforming ability and the quality of the grids. Coupled with 3 - D ALE Euler solver this dynamic unstructured grid method is applied to simulating transonic unsteady flow about a rectangle rigid wing and a high -aspect ratio sweepback wing. The computation results are in good agreement with those of the literatures and experiments.

关 键 词：非结构动网格 弹簧近似 非定常流动 EULER方程 大展弦比后掠机翼 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] O35[理学—流体力学]