Numerical study on boundary layer suction at throat of a CARET inlet

被引：0
|
作者：
He T. [1 ]
Wang Q. [1 ,2 ]
机构：
[1] School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing
[2] Collaborative Innovation Center for Advanced Aero-Engine, Beijing
来源：
| 2018年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 33期
关键词：
Boundary layer suction; CARET inlet; Flow control; Total pressure distortion; Total pressure recovery coefficient;
D O I：
10.13224/j.cnki.jasp.2018.09.026
中图分类号：
学科分类号：
摘要：
To control the flow separation of a CARET inlet, the boundary layer suction slots at the throat of the inlet were designed. The commercial CFD software Fluent was used to simulate the flow field at the design point (Mach number of 2.0). Total pressure recovery and distortion at exit of inlet were used to evaluate the effectiveness of different devices. Simulation results indicated that boundary layer suction in throat can fix the normal shock in the throat and form a stable flow field. It can weaken the shockwave/ boundary layer interaction, suppress flow separation, remarkably increase the total pressure recovery and reduce the total pressure distortion at exit surface of inlet. The front placing slots at the throat section can decrease the distortion of exit surface obviously compared with a rear position. As the suction mass flow increased, the inlet performance firstly became better, and then leveled off. © 2018, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2278 / 2284
页数：6
相关论文
共 18 条
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