湍流模型在复杂流场数值模拟中的应用  

Applications of Turbulence Models in Simulation of Complex Flows

作　　者：肖志祥[1] 李凤蔚[1] 鄂秦[1] 

机构地区：[1]西北工业大学流体力学研究所,陕西西安710072

出　　处：《计算物理》2003年第4期335-340,共6页Chinese Journal of Computational Physics

基　　金：总装备部"十.五"及民机预研资助项目

摘　　要：　采用4种湍流模型:代数Baldwin Lomax(B L)模型、半方程Johnson King(J K)模型的两个版本(J K90A和J K92)以及两方程k g模型,分别数值模拟了导弹超音速流动、NASATND 712标模和民机翼身组合体(两区C O网格)跨音速流动.采用中心有限体积和多步Runge Kutta方法数值积分三维可压缩雷诺平均Navier Stokes(N S)方程组.k g湍流模型方程的求解采用类似于N S方程组的方法进行.所有湍流模型均能很好地模拟附体及小分离流动;对于大攻角、分离剧烈的导弹流动,k g和J K92模型与实验吻合更好;B L模型在模拟民机跨音速流动时,它所捕捉的激波位置较其余3种模型靠后.利用多块网格模拟民机翼身组合体流场时,k g模型的模拟能力强于其余3种模型.Four turbulence models:algebraic BaldwinLomax model with DeganiSchiff modification, two versions of JohnsonKing model (JK90A and JK92) and twoequation kg model, are described and evaluated for missile supersonic flow, NASA TN D712 standard model and the civil airplane wingbody configuration (twoblock CO mesh) transonic flows. The 3D compressible Reynolds averaged NavierStokes (RANS) equations are integrated numerically by central\|difference with artificial viscosity scheme, finite volume formulation and explicit multistep RungeKutta algorithm. The turbulence equations of kg model are explicitly solved in the same way as the RANS. Results show that all models can perform well for attached and mildly separated flows. For large angleofattack separated flow over the missile, kg and JK92 models match the experimental results much better than those with BL and JK90A models. According to the BL model with some modification, the shock location logs behind those with the other three models for the civil airplane geometry. Model kg, because of its advantages such as without using normaltowall distance, simple source terms and straightforward boundary conditions, performs best in the four models for complex configuration with multiblock mesh system or multiwall interference. BL and JK models, despite of cheapness and robustness, both base on empirical Prandtl mixinglength hypothesis and need to calculate the distance normal to the wall, undoubtedly limiting the application scope of these models for multiblock mesh system and complex geometry.

关 键 词：湍流模型 复杂流场 数值模拟 多块网格 翼身组合体 飞机 粘性流场 计算方法 空气动力学 

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]