Effect of three-electrode plasma synthetic jet actuator on shock wave control

被引:31
作者
Zhou, Yan [1 ]
Xia, ZhiXun [1 ]
Luo, ZhenBing [1 ]
Wang, Lin [1 ]
机构
[1] Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China
基金
中国国家自然科学基金;
关键词
plasma synthetic jet; three-electrode; shock wave; active flow control; FLOW-CONTROL; AERODYNAMIC ACTUATION; SUPERSONIC-FLOW; PENETRATION;
D O I
10.1007/s11431-016-0248-4
中图分类号
T [工业技术];
学科分类号
08 ;
摘要
A three-electrode high-energy plasma synthetic jet (PSJ) actuator was used for shock wave control. This actuator is an enhanced version of the two-electrode actuator as a high-voltage trigger electrode is added to increase the cavity volume and the input energy while retaining a relatively low disruptive voltage. The electrical properties were studied using current-voltage measurements, and the energy consumption was calculated. To assess the jet strength, the penetration of PSJ was compared with empirical values, and the results show that the momentum flux ratio of PSJ for a capacitance of 0.96, 1.6, and 3 mu F was approximately equal to 0.6, 1.0, and 1.3, respectively. The interaction of PSJ with shock waves was acquired using high-speed shadowgraph imaging. The shock was generated by a 25A degrees compression ramp in Mach 2 flow, and PSJ actuator was placed up-stream of the compression ramp. Under the action of PSJ, the strength of the shock was notably weakened, and the near-wall part of the shock was entirely eliminated. The results show the good control effect of the three-electrode high-energy PSJ in high-speed flow.
引用
收藏
页码:146 / 152
页数:7
相关论文
共 22 条
  • [1] Plasma Jet for Flight Control
    Anderson, Kellie V.
    Knight, Doyle D.
    [J]. AIAA JOURNAL, 2012, 50 (09) : 1855 - 1872
  • [2] [Anonymous], P 41 AER SCI M EXH
  • [3] Shock wave drag reduction
    Bushnell, DA
    [J]. ANNUAL REVIEW OF FLUID MECHANICS, 2004, 36 : 81 - 96
  • [4] Actuators for Active Flow Control
    Cattafesta, Louis N., III
    Sheplak, Mark
    [J]. ANNUAL REVIEW OF FLUID MECHANICS, VOL 43, 2011, 43 : 247 - 272
  • [5] SparkJet characterizations in quiescent and supersonic flowfields
    Emerick, T.
    Ali, M. Y.
    Foster, C.
    Alvi, F. S.
    Popkin, S.
    [J]. EXPERIMENTS IN FLUIDS, 2014, 55 (12) : 1 - 21
  • [6] Control of mean separation in shock boundary layer interaction using pulsed plasma jets
    Greene, B. R.
    Clemens, N. T.
    Magari, P.
    Micka, D.
    [J]. SHOCK WAVES, 2015, 25 (05) : 495 - 505
  • [7] MIXING AND PENETRATION STUDIES OF SONIC JETS IN A MACH-2 FREESTREAM
    GRUBER, MR
    NEJAD, AS
    CHEN, TH
    DUTTON, JC
    [J]. JOURNAL OF PROPULSION AND POWER, 1995, 11 (02) : 315 - 323
  • [8] Subsonic Jet Mixing via Active Control Using Steady and Pulsed Control Jets
    Kamran, Muhammad A.
    McGuirk, James J.
    [J]. AIAA JOURNAL, 2011, 49 (04) : 712 - 724
  • [9] Kuo S P., 2007, SHOCK WAVES, V17, P225
  • [10] Plasma-assisted combustion of gaseous fuel in supersonic duct
    Leonov, Sergey B.
    Yarantsev, Dmitry A.
    Napartovich, Anatoly P.
    Kochetov, Igor V.
    [J]. IEEE TRANSACTIONS ON PLASMA SCIENCE, 2006, 34 (06) : 2514 - 2525