激波后高温高速流场中的传热特性研究

Analytical study of heat transfer of high-temperature and high-velocity flow field behind shock waves

激波后高温、高速流场中的热力学与传热特性分析是直接涉及到飞行器热防护设计与传热分析的关键问题之一,借助于多组分、考虑非平衡态气体的振动以及激波与热化学非平衡态效应的守恒积分型Navier-Stokes方程组,并用高分辨率总变差减小(TVD)格式进行求解,计算与研究了Apollo工程AS-202返回舱再入地球大气层的6个飞行工况(飞行马赫数15.52～22.63)以及Huygens飞行器再入土卫六大气层的6个工况(飞行马赫数17.29～24.47),分析了不同工况下弓形脱体激波后高温高速流场的热力学与传热特性,计算得到了沿壁面的热流密度分布、温度分布以及Stanton数分布,并与国外相关飞行数据进行了比较,两者吻合较好.相关计算可以指导有关飞行器的热防护设计.

Analytical study of thermodynamics and heat transfer of high-temperature and high-velocity flow field behind shock waves is an important problem involving the design and heat transfer analysis of vehicle thermal protection system （TPS）.The flow fields of the Apollo AS-202 return capsule aviating in the earth atmosphere of six cases （the Mach number varying from 15.52 to 22.63） and the Huygens vehicle aviating in the Titan atmosphere of six cases （the Mach number varying from 17.29 to 24.47） were simulated by using conservation integral form of Navier-Stokes equations with multi-species,nonequilibrium molecular thermal excitation and chemical reactions,based on the high-resolution total variation diminishing （TVD） scheme.Thermodynamics and heat transfer of high-temperature and high-velocity flow field behind bow shock were studied,and the wall heat flux density,wall temperature and Stanton number were in good agreement with the flight data.These results are useful for design of correlative vehicles＇TPS.