绕Apollo飞船的高超声速化学非平衡流动的数值模拟  

NUMERICAL SIMULATION FOR HYPERSONIC FLOW OF NONEQUILIBRIUM GASES AROUND THE APOLLO COMMAND MODULE

作　　者：黎作武[1] 张涵信[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《力学学报》1996年第1期8-22,共15页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金

摘　　要：利用混合通量分裂方法，建立了很方便求解的隐式ＮＮＤ格式，求解了完全气体和化学非平衡空气绕Ａｐｏｌｌｏ飞船的流动，计算结果和实验值作了比较．应用拓扑分析方法，研究了背风区和尾迹内的流动结构．A hybrid flux splitting method is used to develop an implicit NND scheme which possesses good stability characteristics and high converging velocity. The hypersonic flows of the perfect gas and nonequilibrium gas around the Apollo Command Module are simulated with the method by solving the N-S equations. The numerical results agree with the experimental data satisfactorily. The flow structure in the leeside and wake is studied with the topological method.

关 键 词：NND格式 非平衡流动 高超声速流 数值模拟 飞船 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]