摘要
采用雷诺平均Ｎ－Ｓ方程和Ｂ／Ｌ代数湍流模型计算了具有无源控制空腔时正激波／湍流附面层干扰流场。计算与实验结果的比较表明，本文方法可较准确地预测激波结构、激波与附面层干扰区流动基本特征及波后流动分离状态、激波位置、波前马赫数等参数。
A full Navier-Stokes procedure,coupling with a Baldwin/Lomax turbulence model,is used to study the normal shock wave/turbulent boundary layer interaction with passive cavity.In addition,the ventilation velocity profile on the porous plate is calculated by a empirical model formulated from experiments.The total pressure and total temperature boundary conditions for inflow are given due to the existancc of sonic section in the channel flow and the static pressure boundary condition for out flow is given as well.The comparison between numerical and experimental results shows that the presented procedure can predict the shape of the shock,the mach number in front of the shock,the pressure ratio on the wall and position of the shock quite well.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1997年第4期381-384,共4页
Journal of Aerospace Power
关键词
激波
干扰
控制问题
湍流
边界层
数值模拟
Turbulent boundary layer Shock wave interference Control problems Numerical Simulation
