摘要
本文采用一种数值方法设计和分析跨声速翼型。几个算例表明,对于激波/边界层弱干扰和强干扰情形,该方法的结果与风洞实验值吻合良好。但是,当翼型表面出现分离时,两者的差别较大。
A numerical method has been employed to design and analyse airfoils in transonic viscous flow. The results show that the agreement of present method and the wind tunnel experiment is good both for weak interaction cases of shock wave/boundarylayer and for strong cases. When the separation occures, however, the agreement is poor downstream of the shock wave.
出处
《空气动力学学报》
CSCD
北大核心
1989年第2期235-239,共5页
Acta Aerodynamica Sinica
关键词
跨声速势流
粘性流
翼型
边界层
transonic potential flow, boundary layer, airfoil design.
