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.
出处
《力学学报》
EI
CSCD
北大核心
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
关键词
NND格式
非平衡流动
高超声速流
数值模拟
飞船
NND scheme, hybrid flux splitting method, chemically nonequilibrium flow, topological analysis
