高超声速气动热数值模拟中化学非平衡效应  

Developments of Chemical Non-Equilibrium Effects in Numerical Simulation of Aerodynamic Heating in Hypersonic Flow

作　　者：赵一朴 胡雨濛 黄海明 

机构地区：[1]北京交通大学,工程力学研究所,北京

出　　处：《力学研究》2018年第4期126-144,共19页International Journal of Mechanics Research

基　　金：国家自然科学基金项目(11472037,1772042).

摘　　要：当飞行器以高超声速飞行时,其前方的气体剧烈压缩和粘性阻滞引起热障问题。由于高超声速流中非平衡效应对气动热的影响很大,化学非平衡效应成为高超声速气动热领域研究的关键问题之一。本文简要介绍了非平衡效应和真实气体效应,在此基础上,综述了化学非平衡模型下气动热数值模拟的研究进展,包括真实气体效应、化学非平衡效应、化学反应模型、近壁面第一层网格高度对气动热数值模拟结果的影响,以及化学非平衡流条件下圆球高超声速绕流的激波脱体距离随马赫数的变化规律,该规律有待相关风洞试验的验证。文章最后指出湍流对化学非平衡效应的影响及辐射效应对气动热数值模拟的影响是值得关注的研究方向。When the aircraft flies at hypersonic velocity, the intense compression of gas and the viscous block make the temperature rise sharply, which results in “thermal barrier” problem. The chemical non-equilibrium effect becomes one of the key issues in the research of hypersonic aerodynamics as the non-equilibrium effect in hypersonic flow has a great influence on the aerodynamic. Non-equilibrium effect and “real gas effect” are briefly introduced in this thesis. The developments chemical non-equilibrium effects in numerical simulation of aerodynamic heating were reviewed, including chemical non-equilibrium effect, “real gas effect”, chemical reaction model, the first grid spacing. The shock wave standoff distance is numerically simulated by chemical non-equilibrium flow passing a sphere and the relationship between the shock wave standoff distance with Mach number is analyzed, this law needs to be verified by subsequent tests. Finally, it is pointed out that the effect of turbulence on chemical non-equilibrium effect and the effect of radiation on numerical simulation of aerodynamic heating are worthy of attention.

关 键 词：高超声速 气动热 化学非平衡流 网格划分 激波脱体距离 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]