摘要
本文采用时均Ｎ－Ｓ方程和Ｂａｌｄｗｉｎ／Ｌｏｍａｘ代数湍流模型计算了典型拉伐尔喷管内正激波与湍流边界层干扰流场。计算与实验结果的比较表明，方法可准确地预测激波结构，激波与边界层干扰区流动特征，激波位置、激波前马赫数和壁面压力分布等。
In this paper,a full NavierStokes procedure,coupling with a Baldwin/Lomax turbulence model,is used to study the normal shock wave/turbulent boundary layer interaction in a typical supersonic nozzle.The comparison between numerical and experimental results shows that both results agree quite well on shape of the shock,the position of the shock,the Mach number in front of the shock and pressure distribution on the wall.
出处
《空气动力学学报》
CSCD
北大核心
1998年第2期187-191,共5页
Acta Aerodynamica Sinica
关键词
激波
边界干扰
湍流
流场数值模拟
管内流动
shock wave/boundary layer interaction
computation of fluid flow
turbulence
fluid flow in a nozzle
