AUSMPW+格式在高超声速热化学非平衡流数值模拟中的应用  

Applying AUSMPW+ Scheme to Numerical Simulationof Hypersonic Thermochemical Nonequilibrium Flow

作　　者：柳军[1] 曾明[1] 赵慧勇[2] 乐嘉陵[2] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《国防科技大学学报》2002年第6期6-10,共5页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(19889209)

摘　　要：将AUSMPW+格式应用到高超声速热化学非平衡流场的数值模拟中。为提高精度,采用了三阶MUSCL插值方法。与LU SGS方法结合,提高了单步计算效率和收敛性。采用热化学非平衡十一组元气体模型求解了非定常轴对称Navier Stokes方程组,得到了收敛结果。数值模拟结果与文献结果进行了对比,并在弹道靶中进行了钢质圆球的实验验证。计算结果与文献、实验的对比说明,AUSMPW+格式可以在热化学非平衡流的数值模拟中精确地捕捉到强弓形激波,得到准确的空气动力系数。AUSMPW+ scheme is applied to numerical simulation of hypersonic thermochemical nonequilibrium flow. The thirdorder MUSCL scheme is used to get more accurate solutions. The present schemes combined with the LUSGS scheme to improve the efficiency and convergence of computation. Solving axisymmetric NavierStokes equations with 11 species air model gets the convergent solutions of thermochemical nonequilibrium flow. The ballistic range experiment is conducted for code validation and the sphere model is made of steel. The computational results are good compared with the experimental data and reference data. Using AUSMPW+ scheme in numerical simulation of hypersonic thermochemical nonequilibrium flow can get the accuracy aerodynamics and the accuracy position of strong bow shock.

关 键 词：高超声速流 AUSMPW+格式 热化学非平衡 数值模拟 弹道靶实验 高超声速飞行器 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]