摘要
对高超声速热化学非平衡钝体绕流进行研究,发展了高温热化学非平衡条件下的高超声速气动热数值模拟方法。采用二阶精度迎风TVD格式的N-S方程有限体积法多块结构网格求解器,考虑了空气5组分及化学非平衡效应的影响,对组分生成源项及振动能源项采用了点隐式的处理,提高了计算效率。对球锥模型和RAM-CII飞行实验等算例进行了数值气动热模拟,分析了不同非平衡模型在热化学非平衡条件下流场的影响。计算结果表明建立的数值模拟方法具有较高的精度。
Based on the study of hypersonic thermochemical nonequilibrium flow around a blunt body,hy?personic aerothermal simulation method is developed. The second-order accuracy windward TVD format finite volume method of structure grid solver can solve Euler or Navier-Stokes equations, with the solver considering the five components in air and chemical nonequilibrium effect. Vibrational and chemical source terms are calcu?lated implicitly which improves the calculation efficiency. Sphere cone and RAM-CII numerical examples are giv?en on thermochemical nonequilibrium aerothermal simulation. The flow field are discussed with different nonequi?librium models and the computational results show the high accuracy based on comparison with the existing exper?imental data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2014年第12期1585-1591,共7页
Journal of Propulsion Technology
基金
国家自然科学基金(11172055
11202045)
中国博士后科学基金
中央高校基础科研基金(DUT11ZD(G)01)
基本科研业务费专项资金
关键词
高超声速
热化学非平衡
TVD格式
数值模拟
Hypersonic
Thermochemical nonequilibrium
TVD scheme
Numerical simulation
