高超声速喷管三维热化学非平衡流场的数值模拟  

Numerical simulation of three dimensional thermo-chemical nonequilibrium flowfield in hypersonic nozzle

作　　者：李海燕[1] 朱国林[1] 董维中[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1期106-110,共5页Acta Aerodynamica Sinica

基　　金：国家863计划资助项目

摘　　要：利用数值求解三维热化学非平衡Navier-Stokes方程的方法和多块网格技术,数值模拟了典型高焓激波风洞锥型喷管的三维非平衡流场,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、组分N2和O2振动温度、马赫数和组分质量分数在轴对称线上的分布,也给出了喷管出口附近的速度和温度沿径向分布等结果,获得了喷管流场的详细信息,并与已经存在的采用轴对称Navier-Stokes方程计算的结果,进行了比较,二者吻合得很好。计算结果表明:目前的代码是可以模拟多块结构网格下的热化学非平衡流动的。A multi block solver for 3D Navier-Stokes equations include nonequilibrium thermo-chemistry is presented, which has been applied to simulate the thermo-chemical nonequilibrium flow in a conical hypersonic nozzle in high enthalpy facilities. The thermo-chemical nonequilibrium effects are discussed. The results of centerline translational temperature , vibrational temperatures of the species N2 and O2, Mach number, species mass fractions distributions are presented . Temperature and velocity transverse proftles near nozzle exit and other flow information in the nozzle are shown as well. Present results are in good agreement with the existing 2D-axisymmetric Navier-Stokes equations solutions . It is shown that the present cede is capable of simulating thermo-chemical nonequilbrium flow on multi block structured grids.

关 键 词：数值模拟 热化学非平衡流 高超声速喷管 多块流动 三维Navier-Stokes方程 

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]