再入体实验模型热化学非平衡绕流流场的数值分析  

Numerical analysis of thermal and chemical non-equilibrium testing flow-field around the reentry blunt body

作　　者：董维中[1] 高铁锁[1] 张志成[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2008年第2期163-166,共4页Acta Aerodynamica Sinica

基　　金：气动预研基金项目<气动物理特性研究>资助

摘　　要：利用数值求解一个和多个振动温度热化学非平衡Navier-Stokes方程的CFD计算程序,对爆轰风洞球锥试验模型的热化学非平衡绕流流场进行了数值模拟,分析了分子组分振动温度在全流场(头身部流场和底部流场)中的分布规律。研究结果表明:(1)计算的压力、电子数密度以及流场的光辐射数据与试验数据符合较好;(2)在再入体身部,大多数分子的振动温度峰值大大高于平动温度的峰值;在再入体近尾出现振动温度冻结并大大高于平动温度的现象;CO2的两个振动态的振动温度分布非常接近平动温度分布。With the CFD code by solving numerically Navier-Stokes equations, considering the vibrational energy mode of one or multiple vibrational temperatures, numerical simulations were done for thermal and chemical non-equilibrium testing flow-field around the reentry blunt body in the detonation driven shock tunnel, and the analysis was done for molecular vibrational temperature in the flow-field, the following research results are obtained： （1） the computed data are compared well with exper/ment data; （2）for most molecular species, the peak value of vibrational temperature is higher than that of translational temperature at the body of testing model, and the frozen phenomenon of the vibrational temperature appear in the flow of afterbody, but the vibrational temperatures of two mode of CO2 are close to equilibrium mode.

关 键 词：高超声速流动 非平衡流场 气体辐射 振动温度 

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]