| 具有无源控制空腔时正激波/湍流附面层干扰的数值模拟 |
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| 引用本文： | 梁德旺,R．包宁.具有无源控制空腔时正激波/湍流附面层干扰的数值模拟[J].航空动力学报,1997,12(4):381-384. |
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| 作者姓名： | 梁德旺 R．包宁 |
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| 作者单位： | 南京航空航天大学，德国卡尔斯鲁厄大学，南京航空航天大学动力工程系 |
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| 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。
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| 关 键 词： | 激波／干扰 控制问题 湍流边界层 数值模拟 |
| 收稿时间： | 9/1/1996 12:00:00 AM |
| 修稿时间： | 1996/12/1 0:00:00 |
NUMERICAL SIMULATION OF NORMAL SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTION WITH PASSIVE CAVITY |
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| Liang Dewang and R. Bohning.NUMERICAL SIMULATION OF NORMAL SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTION WITH PASSIVE CAVITY[J].Journal of Aerospace Power,1997,12(4):381-384. |
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| Authors: | Liang Dewang and R Bohning |
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| Institution: | 2nd Dept.Nanjing University of Aeronautics and Astronautics,Nanjing 210016;University of Karlsrube Germany |
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| Abstract: | 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. |
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| Keywords: | Turbulent boundary layer Shock wave interference Control problems Numerical Simulation |
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