摘要
对高超声速圆球模型飞行流场进行数值模拟 ,分别采用空气完全气体模型、平衡气体模型以及热化学非平衡 1 1组元气体模型求解非定常轴对称N -S方程组。使用有限差分时间相关法捕捉激波 ,得到了定常流场的解。差分方程隐式部分采用了LU -SGS方法以避免矩阵运算 ,对化学反应和振动能量源项采用预处理矩阵以解决刚性问题。由计算结果处理得到的阴影图和干涉条纹图与再入物理弹道靶实验照片进行了对比分析 ,验证了实验中圆球飞行流场大部分区域接近于平衡状态。
The hypersonic flowfields around the sphere model are simulated numerically by solving axisymmetric Navier-Stokes equations with various thermal and chemical models, such as perfect gas model, equilibrium gas model, and non-equilibrium gas model of two temperatures. The time-dependent finite difference scheme is used to capture the shock. The LU-SGS method is used in implicit part of the difference scheme to avoid matrix operations. The preconditioning technique is used for solving stiffness problem. The computational interferograms and shadowgraphs of equilibrium gas model are good compared with the experimental photos.
出处
《流体力学实验与测量》
CSCD
北大核心
2002年第1期67-73,79,共8页
Experiments and Measurements in Fluid Mechanics
基金
国防自然科学基金资助项目 (1 98892 0 9)
关键词
热化学非平衡
数值模拟
飞行器
实验
高超声速圆模型
飞行流场
numerical calculation
ballistic range
thermochemical nonequilibrium
equilibrium gas
interferogram
shadowgraph
