A Side Wall Flow-Control Method of Supersonic Inlet

被引：0
|
作者：
Zhao Y.-X. [1 ]
Xie L.-R. [1 ]
Wang K. [1 ]
Duan X. [1 ]
Zhang B. [1 ]
机构：
[1] Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2019年 / 40卷 / 12期
关键词：
Boundary interaction; Flow control; Inlet performance; Shock wave; Supersonic inlet;
D O I：
10.13675/j.cnki.tjjs.180607
中图分类号：
学科分类号：
摘要：
To improve the interaction between forebody shock wave and side wall boundary layer of 2-D supersonic inlet, a flow-control method of bleeding on side wall is put forward. The influence rules of typical geometric parameters such as width, position and angle of side wall slit on the performance of the inlet are studied by numerical simulation. The results show that bleeding on side wall decrease spillage of lip corner and improve inlet channel flow field under design Mach number condition. The inlet flow ratio increased by 2.27%, and the inlet throat total pressure recovery coefficient increased by 3.37%. In addition, the performance of inlet is also improved under off-design condition. The research results of typical geometric parameters indicate that performance of the inlet have been improved obviously when side wall slit is located at position of forebody shock wave (L=-1.4~-0.21) and slit width equals 0.85~1.10 times thickness of boundary layer. The effect on the range of slit angle researched can be ignored. © 2019, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：2673 / 2682
页数：9
相关论文
共 12 条
  • [1] Sorensen N.E., Bencze D.P., Possibilities for Improved Supersonic Inlet Performance, Journal of Aircraft, 11, 5, pp. 288-293, (1974)
  • [2] Weiss J., Chokani N., Quiet Tunnel Experiments of Shockwave/Turbulent Boundary Layer Interaction
  • [3] Knight D., Mortazavi M., Hypersonic Shock Wave Transitional Boundary Layer Interactions-A Review, The 47th AIAA Fluid Dynamics Conference, (2017)
  • [4] Liepmann H.W., The Interaction Between Boundary Layer and Shock Waves in Transonic Flow, Journal of the Aeronautical Sciences, 13, 12, pp. 623-637, (1946)
  • [5] Wu M., Pino M.M., Direct Numerical Simulation of Shockwave/Turbulent Boundary Layer Interaction
  • [6] Deng X.Y., Settles G.S., A Test of the Independence Principle in Swept Cylindrical Shock Wave/Turbulent Boundary Layer Interactions, Acta Aeronautica Sinica, 7, 4, pp. 442-448, (1989)
  • [7] Hamed A., Shang J.S., Survey of Validation Data Base for Shockwave Boundary-Layer Interactions in Supersonic Inlets, Journal of Propulsion and Power, 7, 4, pp. 617-625, (1991)
  • [8] Do H., Im S., Mungal M.G., Et al., The Influence of Boundary Layers on Supersonic Inlet Unstart
  • [9] Harloff G.J., Smith G.E., Supersonic-Inlet Boundary-Layer Bleed Flow, AIAA Journal, 34, 4, pp. 778-785, (1996)
  • [10] Yan H.-M., Zhong J.-J., Han J.-A., Et al., Research on Boundary-Layer Suction in the Throat of Supersonic Inlet, Journal of Propulsion Technology, 30, 2, pp. 176-181, (2009)
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