非结构网格的高超声速粘性MHD流场数值模拟  

Numerical Simulation of Hypersonic Viscous MHD Flows Based on Unstructured Meshes

作　　者：潘勇[1] 王江峰[1] 伍贻兆[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《南京航空航天大学学报》2007年第5期555-559,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(10402013)资助项目

摘　　要：应用数值方法在非结构网格上对磁场干扰下的二维高超声速钝头体粘性绕流进行了数值模拟。控制方程为N-S方程耦合Maxwell方程的粘性MHD方程组,空间离散采用有限体积方法,对流项用AUSM格式计算,粘性项用中心格式求解,时间推进用显式5步Runge-Kutta格式,引用双曲型散度清除技术加强▽.B=0的条件。计算模型为二维钝头体,在高超声速来流条件下,分别对有、无均匀磁场干扰下的流动进行了数值模拟。计算结果表明,在均匀磁场干扰下,激波脱体距离显著增加,物体表面压力急剧下降。对比表明文中发展的计算方法可以准确地进行二维粘性MHD流场的数值模拟。Two-dimensional hypersonic viscous flows around a blunt body with the effects of magnetic field are numerically investigated on unstructured meshes. The governing equations are 2-D viscous MHD（magnetohydrodynamics） equations. The finite volume method（FVM） is implemented in the spatial discretization, and the convective fluxes are evaluated by AUSM scheme and the viscous fluxes are calculated by the central scheme. An explicit 5-stage Runge-Kutta scheme is used for the time integration. Hyperbolic divergence cleaning technique is introduced to enhance ▽· B： 0. 2-D hypersonic viscous plasma flows around a blunt body with or without the effects of a uniform magnetic field are numer- ically simulated. Results show the great differences between those two situations. With the effects of magnetic field, the shock stand off distance increases greatly and the pressure on the body surface decreases a lot. Compared with the limited references, the result shows the accuracy of the numerical method developed in this paper.

关 键 词：非结构网格 粘性MHD方程 AUSM格式 高超声速绕流 

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] O354.4[理学—流体力学]