高超声速喷管非平衡尺度效应的数值分析  

Numerical analysis of non-equilibrium scale effects in hypersonic nozzle

作　　者：曾明[1] 林贞彬[1] 冯海涛[2] 瞿章华[2] 

机构地区：[1]中国科学院力学研究所,北京100080 [2]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2005年第1期38-41,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金 (90205027)。

摘　　要：采用轴对称热化学非平衡全N S方程, 数值分析了高超声速喷管流场中非平衡引起的尺度效应。并给出计算条件下喷管轴线上的物理量和化学组元分布。计算结果表明, 在喉部下游不远处流动趋近于化学冻结和热力冻结状态。流场 (特别是核心无粘流区) 的特性不仅取决于流动尺度的相对值, 也取决于其绝对值。Using axisymmetric full Navier-Stokes equations, the thermochemical nonequilibrium flow in hypersonic nozzle was simulated and the scale effects due to nonequilibrium were analysed numerically. The flow properties including chemical species distribution along axis of the nozzle were also presented. The results show that the flow tends to be in thermal and chemical frozen not far from throat. Flow characteristics, especially in inviscid region, are determined by absolute value as well as relative value of scale.

关 键 词：高超声速飞行器 喷管 非平衡流 尺度效应 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]