中国物理B ›› 2014, Vol. 23 ›› Issue (7): 75210-075210.doi: 10.1088/1674-1056/23/7/075210

• PHYSICS OF GASES, PLASMAS, AND ELECTRIC DISCHARGES • 上一篇    下一篇

Shockwave-boundary layer interaction control by plasma aerodynamic actuation：An experimental investigation

孙权, 崔巍, 李应红, 程邦勤, 金迪, 李军   

  1. Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi'an 710038, China
  • 收稿日期:2013-12-17 修回日期:2014-03-07 出版日期:2014-07-15 发布日期:2014-07-15
  • 基金资助:
    Project supported by the Key Program of the National Natural Science Foundation of China (Grant No. 51336011) and the National Natural Science Foundation of China (Grant Nos. 51207169 and 51276197).

Shockwave-boundary layer interaction control by plasma aerodynamic actuation：An experimental investigation

Sun Quan (孙权), Cui Wei (崔巍), Li Ying-Hong (李应红), Cheng Bang-Qin (程邦勤), Jin Di (金迪), Li Jun (李军)   

  1. Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi'an 710038, China
  • Received:2013-12-17 Revised:2014-03-07 Online:2014-07-15 Published:2014-07-15
  • Contact: Sun Quan E-mail:steve5761@126.com
  • About author:52.50.Nr; 52.80.Mg; 47.80.Jk
  • Supported by:
    Project supported by the Key Program of the National Natural Science Foundation of China (Grant No. 51336011) and the National Natural Science Foundation of China (Grant Nos. 51207169 and 51276197).

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摘要： The potential of controlling shockwave-boundary layer interactions (SWBLIs) in air by plasma aerodynamic actuation is demonstrated. Experiments are conducted in a Mach 3 in-draft air tunnel. The separation-inducing shock is generated with a diamond-shaped shockwave generator located on the wall opposite to the surface electrodes, and the flow properties are studied with schlieren imaging and static wall pressure probes. The measurements show that the separation phenomenon is weakened with the plasma aerodynamic actuation, which is observed to have significant control authority over the interaction. The main effect is the displacement of the reflected shock. Perturbations of incident and reflected oblique shocks interacting with the separation bubble in a rectangular cross section supersonic test section are produced by the plasma actuation. This interaction results in a reduction of the separation bubble size, as detected by phase-lock schlieren images. The measured static wall pressure also shows that the separation-inducing shock is restrained. Our results suggest that the boundary layer separation control through heating is the primary control mechanism.

关键词: shock, boundary layer, plasma, flow control

Abstract: The potential of controlling shockwave-boundary layer interactions (SWBLIs) in air by plasma aerodynamic actuation is demonstrated. Experiments are conducted in a Mach 3 in-draft air tunnel. The separation-inducing shock is generated with a diamond-shaped shockwave generator located on the wall opposite to the surface electrodes, and the flow properties are studied with schlieren imaging and static wall pressure probes. The measurements show that the separation phenomenon is weakened with the plasma aerodynamic actuation, which is observed to have significant control authority over the interaction. The main effect is the displacement of the reflected shock. Perturbations of incident and reflected oblique shocks interacting with the separation bubble in a rectangular cross section supersonic test section are produced by the plasma actuation. This interaction results in a reduction of the separation bubble size, as detected by phase-lock schlieren images. The measured static wall pressure also shows that the separation-inducing shock is restrained. Our results suggest that the boundary layer separation control through heating is the primary control mechanism.

Key words: shock, boundary layer, plasma, flow control

中图分类号:  (Plasma heating by DC fields; ohmic heating, arcs)

  • 52.50.Nr
52.80.Mg (Arcs; sparks; lightning; atmospheric electricity) 47.80.Jk (Flow visualization and imaging)