三角翼涡破裂的高精度数值模拟  

High-Order Numerical Simulation of Vortex Breakdown on Delta Wing

作　　者：王光学[1] 邓小刚[1] 王运涛[1] 刘化勇[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《计算物理》2012年第4期489-494,共6页Chinese Journal of Computational Physics

基　　金：国家重点基础研究发展计划(2009CB723801);重点实验室研究基金(JBKY11010200)资助项目

摘　　要：采用5阶精度的加权紧致非线性格式(WCNS-E-5)数值模拟65°后掠角尖前缘三角翼的大攻角跨声速绕流流场,考察低耗散、高分辨率的WCNS-E-5格式对于三角翼涡破裂模拟的适用性,及激波旋涡干扰对涡破裂点位置的影响,重点研究三角翼大攻角旋涡破裂点的突然前移.通过求解任意坐标系下的非定常雷诺平均N-S方程,采用WCNS-E-5和SST两方程湍流模型,与试验结果和文献计算结果对比,表明既有高阶精度又能光滑捕捉激波的WCNS格式在模拟三角翼旋涡破裂方面具有一定优势,其数值结果与试验结果吻合较好,三角翼大攻角旋涡破裂点的突然前移是由于跨声速流场的激波旋涡干扰.With a fifth-order weighted compact nonlinear scheme （WCNS-E-5） , flow field of a 65° delta wing with sharp leading edges at high angles of incidence is simulated. The target is checking WCNS＇ s ability for vortex flow at high angles of incidence and vortex breakdown location with shock-vortex interaction. We focus on sudden jump in breakdown towards apex. Unsteady Reynolds averaged Navier-Stokes（URANS） method is available including a high-order weighted compact nonlinear scheme and an SST turbulence model. It is shown that the high order scheme（WCNS-E-5） with minimum numerical dissipation and could capture discontinuities for high angles of incidence transonic flow of delta wing and the results are matched satisfactorily with experiments. Shock-vortex interaction in transonic freestream explains sudden movement of vortex breakdown as the angle of incidence is increased.

关 键 词：三角翼 加权紧致非线性格式 大攻角 跨声速流动 数值模拟 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]