摘要
针对滑移流区化学非平衡流中的气动热环境预测问题,采用多组分化学非平衡纳维-斯托克斯(N-S)方程对轨道验证飞行器(OREX)进行数值模拟,对比了有限催化和非催化、滑移和无滑移壁面条件下的气动加热,研究了壁面催化和滑移效应对气动热的影响规律,并分析了影响气动热的主要机制。结果表明:壁面催化和滑移效应均会影响流场物理量分布,高度为92.82 km时对激波脱体距离的影响较为明显;随着高度减小,有限催化与非催化壁面间的热流偏差增大,而滑移与无滑移壁面间的热流偏差减小;高度低于92.82 km时有限催化壁面计算得到的驻点热流值与飞行数据吻合较好,偏差均在11%以内;机制分析发现,催化效应对壁面附近的组分分布影响较大,滑移边界条件中的温度跳跃条件对壁面附近的温度分布影响显著。
Numerical simulation predicting the aero-heating of chemical non-equilibrium flow in the slip flow regime has been carried out for the Orbital Reentry Experiment(OREX)vehicle by solving multicomponent chemical nonequilibrium Navier-Stokes(N-S)equations.A detailed comparison is made between the finite rate catalytic and noncatalytic,slip and no-slip wall conditions,and the influence of surface catalysis and slip effects on aero-heating is stud⁃ied.The main mechanism affecting aero-heating is also analyzed.The results show that surface catalysis and slip ef⁃fects influence the distribution of flow properties,with a strong impact on the shock stand-off distance at 92.82 km.With the decrease in altitude,the gap of heat flux increases between the finite rate catalytic and non-catalytic wall con⁃ditions,while decreases between the slip and no-slip wall conditions.At an altitude lower than 92.82 km,the stagna⁃tion point heat flux of the finite rate catalytic wall agrees well with the flight data,with the deviation within 11%.In the area near the wall,the catalytic effect has a considerable influence on species distribution,while the temperature jump condition of slip effects exerts a significant impact on the temperature distribution.
作者
刘重晓
王江峰
LIU Chongxiao;WANG Jiangfeng(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2023年第16期101-114,共14页
Acta Aeronautica et Astronautica Sinica
基金
江苏高校优势学科建设工程(PAPD)。
关键词
高超声速
化学非平衡
壁面催化条件
滑移效应
气动热环境
hypersonic
chemical non-equilibrium
surface catalysis
slip effects
aero-heating enviroment
