摘要
本文将拉伸变换引入Hosny的高超声速粘性激波层的数值求解方法中,数值计算结果与Little所给出的实验结果相符合。从而不论在雷诺数范围上,或在后身流场的推进计算上,本方法均比Hosny原方法有明显改进。
In the present paper a mesh stretching transformation is introduced into the numerical integrating method for the hypersonic vis-cous shock layer presented by Hosny, M. W[10]. The present method is a little advanced than the Hosny's method in that it can solve the hyper-sonic viscous shock layer flow field for more high Reynolds number and it can march more far along the slender blunt bodies. The numerical results obtained here compare well with the experimental results of Little[12].
出处
《空气动力学学报》
CSCD
北大核心
1989年第3期291-297,共7页
Acta Aerodynamica Sinica
关键词
高超声速
流场
粘性流
激波层
high Reynolds number, mesh stretching transformation , hypersonic flow, viscous shock layer.
