三维粘性激波层方程隐式通量向量分裂求解  

Implicit Flux Vector Splitting Solution of Three-Dimensional Viscous Shock-Layer Equations

作　　者：聂赟[1] 马大为[1] 乐贵高[1] 

机构地区：[1]南京理工大学机械学院,江苏南京210094

出　　处：《战术导弹技术》2013年第2期21-24,共4页Tactical Missile Technology

基　　金：国防基础科研项目(项目编号)B2620110005

摘　　要：针对压缩拐角流动等高超声速飞行器空气动力学中激波与边界层主导的粘性效应问题,采用隐式格式的通量向量分裂方法,在物面坐标系内求解三维无量纲双曲抛物型粘性激波层方程组。给出了二维轴对称亚跨声速喷管内流场的计算结果,包括速度矢量分布和压力、马赫数等值线分布。同时,给出了喷管内外流及其混合尾流的计算结果,包括速度矢量分布和压力、密度、马赫数等值线分布。By the use of implicit flux-vector-splitting method, three-dimensional dimensionless hyperbolic-parabolic viscous shock-layer equations are solved in general curved coordinates system. It can be used to solve the flow field of shock wave/boundary layer interaction, such as compressed corner flow. An axisymmetric sub-tran-supersonic internal flow field solution of a nozzle is given including flow vector distribution, pressure and Mach number contour line distribution. An inner and outer flow field solution of a nozzle and its mixing wake flow is also presented inside being compose of flow vector distribution, pressure, density and Mach number contour line distribution.

关 键 词：通量向量分裂 粘性激波层方程 流场 

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]