高超声速喷管非平衡黏性流动的数值研究  

Numerical Simulation of Non-equilibrium Viscous Flows in Hypersonic Nozzles

作　　者：李海燕[1] 董维中[1] 朱国林[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：《航空学报》2006年第2期204-207,共4页Acta Aeronautica et Astronautica Sinica

基　　金：国家863计划资助项目

摘　　要：分别采用平衡气体模型、化学非平衡气体模型和热化学非平衡气体模型,通过求解轴对称Navier-Stokes方程组,数值模拟了法国Marseille高焓激波风洞锥型喷管(H0=10·3MJ/kg),分析了热化学非平衡效应对喷管流动的影响,给出了平动温度、振动温度、马赫数和组分质量数在轴对称线上的分布与喷管出口附近的速度和温度沿径向分布等结果。计算结果表明:化学反应速度加快,会导致喷管出口温度增加,振动能的冻结会导致喷管出口温度降低。The flow in the conical nozzle of Marseille shock tube tunnel （Ho -10.3 MJ/kg） is computed by solving 2D-axisymmetric laminar Navier-Stokes equations. The numerical analysis includes computations assuming a chemical / thermal equilibrium, chemical nonequilibrium / themal equilibrium and chemical / thermal nonequilibrium nozzle expansions. The thermochemical nonequilibrium effects are discussed. The results of centerline translational rotational temperature, vibrational temperature, Mach number, species mass fraction distributions and temperature and velocity transverse profiles near nozzle exit are presented. It is shown that the exit temperature can be increased when speeding up the chemical reaction process. The freezing of vibrational energy can result in a decrease of the exit temperature.

关 键 词：高超声速喷管 黏性流动 数值模拟 轴对称Navier-Stokes方程组 热化学非平衡效应 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]