高温化学非平衡效应对高超声速飞行器气动力/热影响的数值研究进展  

Progress in the numerical study on the aerodynamic and thermal characteristics of hypersonic vehicles:High-temperature chemical non-equilibrium effect

作　　者：莫凡 高振勋[1,2] 蒋崇文 李椿萱[1,2] MO Fan;GAO ZhenXun;JIANG ChongWen;LEE Chun-Hian(School of Aeronautic Science&Engineering,Beihang University,Beijing 100191,China;Laboratory of Aero-thermal Protection Technology for Aerospace Vehicles,China Aerospace Science and Technology Corporation,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国航天科技集团公司航天飞行器气动热防护实验室,北京100191

出　　处：《中国科学：物理学、力学、天文学》2021年第10期22-37,共16页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家数值风洞工程项目(编号:NNW2018-ZT3A05);国家自然科学基金(编号:11872094)资助项目。

摘　　要：本文主要针对高温化学非平衡效应对高超声速飞行器气动力热影响的数值研究进行了综述.首先分析了高温化学非平衡流动数值模拟中的物理化学模型影响,发现组分扩散系数模型会对完全催化壁条件下的气动热结果产生影响;不同化学动力学模型对于激波/激波干扰等复杂流动区域预测的热流峰值差距甚至高达20%以上.壁面催化效应对气动热影响显著,有限催化模型目前仍在发展当中,其中运用气固表面有限速率化学反应动力学方法得到催化反应速率的模型更具发展潜力.材料烧蚀会在边界层内引入质量引射效应,同时热解气体还会与边界层中的高温空气组分发生复杂化学反应,总体上会显著降低气动热.高温化学非平衡效应对飞行器表面压强的影响主要存在两种机制:一种是激波后比热比变小会引起波后压强增大;另一种是脱体激波角变小进而减小波后压强,对航天飞机、返回舱等典型外形的升/阻力影响相对较小,而对力矩影响较大.最后,高温化学非平衡效应对高超声速湍流边界层的脉动特性产生影响,同时使壁面摩阻增加而热流降低,但并未改变湍流边界层的速度、密度、温度和组分浓度的标度律.In this paper,the progress in the numerical study of high-temperature chemical non-equilibrium effects on the aerodynamic and thermal characteristics of hypersonic vehicles is reviewed.First,the influence of physicochemical models on the numerical simulation of high-temperature chemical non-equilibrium flow is analyzed.The results show that the diffusion coefficient model will affect the aerodynamic heating under the full catalytic wall;the difference between the predicted heat flux peak values of different chemical kinetic models for complex flow areas,such as in the case of shock wave/shock wave interference is greater than 20%.The wall catalytic effect on the aerodynamic heating is considerable.Finite catalytic models are still under development;among them,models using finite-rate chemical reaction kinetic methods for the gas-solid surface to obtain catalytic reaction rates have greater developmental potential.Material ablation introduces the mass injection effect into the boundary layer,while pyrolysis gases result in complex chemical reactions with the high-temperature air in the boundary layer,significantly reducing the overall aerodynamic heating.There are two main mechanisms of high-temperature chemical non-equilibrium effect on the surface pressure of aircraft.One is that the decrease in the specific heat ratio after the shock wave will cause an increase in pressure after the shock wave,and the other is that the decrease of detached shock wave angle will reduce the pressure after the shock wave.Although the high-temperature chemical non-equilibrium effect on the lift and drag of typical shapes,such as space shuttle and re-entry capsule,is relatively small,the effect on the moment is considerable.Finally,high-temperature chemical non-equilibrium affects the fluctuation characteristics of the physical quantity in the hypersonic turbulent boundary layer and increases the wall friction while reducing the heat flux;however,it does not change the scaling laws of velocity,density,temperature,and component conce

关 键 词：高超声速 化学非平衡 催化/烧蚀 气动力/热 湍流边界层 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]