气体模型对高超声速再入钝体气动参数计算影响的研究  

Thermal and chemical model effect on the calculation of aerodynamic parameter for hypersonic reentry blunt body

作　　者：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》2001年第2期197-202,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目! (198892 0 9)

摘　　要：本文采用完全气体模型、振动激发气体模型、平衡气体模型、一温度非平衡气体模型、两温度非平衡气体模型和三温度非平衡气体模型进行了钝体高超声速绕流流场的数值计算。分析了各种气体模型对激波脱体距离、壁面热流、温度分布和密度分布等的影响。结果表明 :采用两温度 (或三温度 )非平衡气体模型计算的激波脱体距离更接近实验情况 ;采用平衡气体模型计算的壁面热流最高 ,一温度非平衡气体模型完全非催化的壁面热流最低 ,而完全气体模型的壁面热流在两者之间。The flowfields around the reentry blunt body are simulated numerically by solving the Navier Stokes with the various thermal and chemical model, such as perfect gas model, vibrational excitation model, equilibrium gas model, and the non equilibrium gas model of one temperature, two temperature and three temperature. It is analyzed that the thermal and chemical model have a effect on the shock detached distance, heat transfer rate, the distributions of temperature and density. The results of analysis show that the shock detached distance computed by two temperature model or three temperature compare well with the experiment data, and the heat transfer rate is highest for one temperature model with non catalytic wall, and lowest for equilibrium gas model, and the heat transfer rate for perfect gas model is between the non catalytic wall and fully catalytic wall . Finally, the contour of density are shown in this paper.

关 键 词：激波脱体距离 热化学模型 气体模型 气动参数 高超声速 空气动力学 飞行器 

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]