振动矩形机翼非线性绕流数值研究  

A Research on the Numerial Value of the Nonlinear Flow of the Oscillating Rectangular Wing

作　　者：郭正[1] 谭杰 刘君[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]湖南省邮政信息技术局,湖南长沙410016

出　　处：《国防科技大学学报》2005年第4期13-17,44,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(90205027;10176037)

摘　　要：发展了可用于模拟包含运动边界的非定常流动的数值方法。该方法采用非结构动网格技术并构造了一种MUSCL类型有限体积格式,求解考虑了动网格效应的三维非定常Euler方程。非结构网格的变形运动由弹簧近似技术实现。用上述方法计算了作正弦振动的矩形机翼非线性绕流,计算结果与实验结果吻合,得到了流体运动与固体运动耦合的非线性流动特性。计算表明,该数值方法具有较好的精度和可靠性,完全可用于气动弹性或其他流固耦合问题的数值模拟。A numerical method is developed to simulate the unsteady flows involving moving botmdaries. For tiffs method, dynamic unstructured grid technique was used, and a MUSCL type finite volume scheme was constructed to discretize the 3D unsteady Euler equations described in ALE frame. The deformation of unstructured grid was implemented by spring analogy. The whole methodology was then applied to simulate the unsteady transonic flow of the three-dimensional rigid wing tmdergoing a forced sinusoidal motion in angle of attack. Computational results are in agreement with the experimental data, and the nonlinear flow characteristics caused by the fluid and structure interaction was clearly obtained. It can be concluded from the research that the whole methodology presented here is adequately accurate and reliable, and can be applied in aeroelasticity study and a series of fluid and structure interaction problems.

关 键 词：非结构动网格 振动机翼 运动边界 EULER方程 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]