流动控制

DBD涡流发生器及其在角区流动控制中的数值研究

  • 徐向南 ,
  • 张华 ,
  • 胡波
展开
  • 北京航空航天大学 航空科学与工程学院 教育部流体力学重点实验室, 北京 100083
徐向南 男,硕士。主要研究方向:流动控制。E-mail:huilieri@163.com;胡波 男,博士研究生。主要研究方向:旋涡与分离流动,流动控制。E-mail:hubohubo666@163.com

收稿日期: 2015-10-21

  修回日期: 2016-01-05

  网络出版日期: 2016-01-11

基金资助

国家自然科学基金(11372027)

Numerical study of DBD vortex generator and application in junction flow control

  • XU Xiangnan ,
  • ZHANG Hua ,
  • HU Bo
Expand
  • Ministry-of-Education Key Laboratory of Fluid Mechanics, School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received date: 2015-10-21

  Revised date: 2016-01-05

  Online published: 2016-01-11

Supported by

National Natural Science Foundation of China (11372027)

摘要

为明确介质阻挡放电(DBD)涡流发生器对马蹄涡的影响,在采用唯象模型的基础上,通过数值方法研究了DBD涡流发生器诱导产生流向涡的结构特性及其对马蹄涡的控制特性。研究结果表明,流动在激励器上游边缘处形成羊角涡,自由剪切层卷入流向涡的涡核并为其提供持续涡量;在柱体根部角区流动中,当对称面两侧激励器诱导流动指向对称面,诱导涡与马蹄涡环绕方向相反时,马蹄涡可以得到有效抑制,反之,则控制效果不佳。最后得出,诱导涡对下游马蹄涡的控制机制体现在其黏性扩散作用、掺混作用以及低压效应3个方面。

本文引用格式

徐向南 , 张华 , 胡波 . DBD涡流发生器及其在角区流动控制中的数值研究[J]. 航空学报, 2016 , 37(6) : 1743 -1752 . DOI: 10.7527/S1000-6893.2016.0006

Abstract

In order to explore the effects of dielectric barrier discharges (DBD) vortex generator on the horseshoe vortex, the phenomenological model is applied in the paper to the numerical simulation. The characteristics of the streamwise vortex structure and its control on the horseshoe vortex are analyzed. The results indicate that the tornado-like vortex is formed at the edge of the upstream electrode, and streamwise vortex engulfs the free shear layer and gains continuous vortices. When the induced flows on the two sides of symmetry plane point to the symmetry and the direction of the induced vortex is opposite to the horseshoe vortex, the strength of horseshoe vortex can be suppressed effectively in junction flow at the root of the cylinder. Otherwise the control effect is poor. Three factors, the viscous diffusion of the induced vortex on horseshoe vortex, and the mixing and low pressure of the induced vortex, related to the control mechanism are pointed out.

参考文献

[1] POST M L, CORKE T C. Separation control on high angle of attack airfoil using plasma actuators[J]. AIAA Journal, 2004, 42(11):2177-2184.
[2] ZHANG P F, LIU A B, WANG J J. Aerodynamic modification of a NACA 0012 Airfoil by trailing-edge plasma gurney flap[J]. AIAA Journal, 2009, 47(10):2467-2474.
[3] 毛枚良, 江定武, 陈亮中, 等. 受DBD等离子体控制的低速流动数值模拟方法研究[J]. 空气动力学学报, 2011, 29(2):129-134. MAO M L, JIANG D W, CHEN L Z, et al. Study of numerical simulation method for low speed flow with DBD plasma[J]. Acta Aerodynamica Sinica, 2011, 29(2):129-134(in Chinese).
[4] OPAITS D F, ROUPASSOV D V, STARIKOVSKAIA S M, et al. Plasma control f boundary layer using low-temperature non-equilibrium plasma of gas discharge[J]. AIAA Journal, 2005, 43(6):1-6.
[5] THOMAS F O, KOZLOV A, CORKE T C. Plasma actuators for cylinder flow control and noise reduction[J]. AIAA Journal, 2008, 46(8):1921-1931.
[6] KOZLOV A V, THOMAS F O. Plasma flow control of cylinders in a tandem configuration[J]. AIAA Journal, 2011, 49(10):2183-2193.
[7] 吴云, 李应红. 等离子体流动控制研究进展与展望[J]. 航空学报, 2015, 36(2):381-405. WU Y, LI Y H. Progress and outlook of plasma flow control[J]. Acta Aeronautica et Astronautica, 2015, 36(2):381-405(in Chinese).
[8] 聂万胜, 程钰锋, 车学科. 介质阻挡放电等离子体流动控制研究进展[J]. 力学进展, 2012, 42(6):722-734. NIE W S, CHENG Y F, CHE X K. A review on dielectric barrier discharge plasma flow control[J]. Advances in Mechanics, 2012, 42(6):722-734(in Chinese).
[9] 李应红, 吴云. 等离子体流动控制技术研究进展[J]. 空军工程大学学报:自然科学版, 2012, 13(3):1-5. LI Y H, WU Y. Progress of research on plasma flow control technology[J]. Journal of Air Force Engineering University:National Science Edition, 2012, 13(3):1-5(in Chinese).
[10] ROTH J R, SHERMAN D M, WILKINSON S P. Electrohydrodynamic flow control with a glow-discharge surface plasma[J]. AIAA Journal, 2000, 38(7):1166-1172.
[11] RIHERD M, ROY S, VISBAL M. Numerical investigation of serpentine plasma actuators for paration control at low Reynolds number:AIAA-2011-3990[R]. Reston:AIAA, 2011.
[12] RIHERD M, ROY S. Serpentine geometry plasma actuators for flow control[J]. Journal of Applied Physics, 2013, 114(8):083303-1-13.
[13] RIZZETTA D P, VISBAL M R. Numerical investigation of plasma-based control for low-Reynolds-number airfoil flows[J]. AIAA Journal, 2011, 49(2):411-425.
[14] OKITA Y, JUKES T, CHOI K S, et al. Flow reattachment over an airfoil using surface plasma actuator:AIAA-2008-4203[R]. Reston:AIAA, 2008.
[15] SCHATZMAN D M, THOMAS F O. Turbulent boundary-layer separation control with single dielectric barrier discharge plasma actuators[J]. AIAA Journal, 2010, 48(8):1620-1634.
[16] JUKES T N, CHOI K S. Dielectric-barrier-discharge vortex generators:Characterization and optimization for flow separation control[J]. Experiments in Fluids, 2012, 52(2):329-345.
[17] JUKES T N, CHOI K S. On the formation of streamwise vortices by plasma vortex enerators[J]. Journal of Fluid Mechanics, 2013, 733:370-393.
[18] SHYY W, JAYARAMAN B, ANDERSSON A. Modeling of glow discharge-induced fluid dynamics[J]. Journal of Applied Physics, 2002, 92(11):6434-6443.
[19] 张攀峰, 刘爱兵, 王晋军. 基于唯象模型的等离子激励诱导流场数值模拟[J]. 北京航空航天大学学报, 2010, 36(1):52-56. ZHANG P F, LIU A B, WANG J J. Numerical simulation on flow induced by plasma actuator based on phenomenological model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(1):52-56(in Chinese).
[20] 吴星钢. 基于二维/三维沟槽的角区流动控制实验研究[D]. 北京:北京航空航天大学, 2014:23-49. WU X G. Experimental study on junction flow control based on two & three dimensional cavity[D]. Beijing:Beihang University, 2014:23-49(in Chinese).
[21] WEI Q D, CHEN G, DU X D. An experimental study on the structure of juncture flows[J]. Journal of Visualization, 2001, 3(4):341-348.
[22] JEONG J, HUSSAIN F. On the identification of a vortex[J]. Journal of Fluid Mechanics, 1995, 285(4):69-94.
[23] 夏雪湔, 邓学蓥. 工程分离流动力学[M]. 北京:北京航空航天大学出版社, 1991:13-50. XIA X J, DENG X Y. Engineering separated flow dynamics[M]. Beijing:Beihang University Press, 1991:13-50(in Chinese).
[24] DEVENPORT W J, SIMPSON R L. Time-dependent and time-averaged turbulence structure near the nose of a wing-body junction[J]. Journal of Fluid Mechanics, 1989, 210(1):23-55.

文章导航

/