翼型、机翼非定常运动模式下动态数值模拟  

Numerical simulation of unsteay flowfield around moving airfoils and wings

作　　者：叶露[1] 王元元[2] 肖艳平[1] 

机构地区：[1]中国民航飞行学院飞行技术学院,广汉618307 [2]西北工业大学航空学院,西安710072

出　　处：《应用力学学报》2011年第5期539-542,559,共4页Chinese Journal of Applied Mechanics

摘　　要：基于RANS方程,通过刚性动网格技术实现对翼型和机翼典型运动模式的描述,采用双时间推进方法和Roe空间离散格式对流场求解,构建了一个非定常气动计算平台;以NACA0012翼型为算例进行了动态数值模拟可信度验证。数值模拟结果与试验数据吻合较好,升力和俯仰力矩的最大计算误差分别为3%和10%,表明了该平台的可靠性。另外,还数值模拟了M6机翼的动态非定常流场,并分析了两种湍流模型对非定常流场激波的捕捉能力。结果表明非定常流动中S-A湍流模型对激波的捕捉较B-L模型更敏感。文中开发的非定常计算平台对进一步解决三维复杂流场的流动问题有很高的工程应用价值。An unsteady numerical simulation platform is developed based on Reynolds-Averaged Navier-Stokes equations.In this computational platform,typical motion pattern of airfoil and wing is described by rigid moving mesh technology,and the flowfield is solved by dual time stepping method and Roe spatial discretization scheme.Then the dynamic flowfield around NACA0012 airfoil is computed to test the reliability of the computational platform.The computation results accord with the experimental data well,the maximal computing errors of lifting and pitching moment coefficient are respectively 3 percent and 10 percent.Furthermore,the unsteady computational platform is applied to solve the unsteady flowfield around M6 wing,and the capability of catching the unsteady flow shock wave of two turbulence models is compared.This unsteady numerical simulation platform can play a very important role in solving complicated 3D unsteady flow problems.

关 键 词：翼型 机翼 非定常数值模拟 动态失速 减缩频率 湍流模型 刚性动网格技术 

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]