High-frequency counter-flow plasma synthetic jet actuator and its application in suppression of supersonic flow separation

Wang, Hongyu; Li, Jun; Jin, Di; Tang, Mengxiao; Wang, Yun; Xiao, Lianghua

doi:10.1016/j.actaastro.2017.10.023

Cited by 38 publications

(10 citation statements)

References 31 publications

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“…Separation control at moderate-Reynolds number ONERA; Xiamen University; UNINA [35,72,73] Jet noise control ONERA [12,74,75] Shock wave/boundary layer interaction control UT Austin; AFEU; NUDT [18,[76][77][78][79][80][81][82][83] In separation control cases, PSJs are typically issued upstream of the separation region, either in the wall-normal direction to create a quasi-streamwise counter-rotating vortex pair [84] or pitched and skewed with respect to the main flow to produce a single dominant streamwise vortex [12]. These vortices transport the high-momentum flow from the outer boundary layer to the near-wall region, resulting in a fuller boundary layer velocity profile and a reduction in boundary layer shape factor (1.3-1.2 in [84]).…”

Section: Institutions Representative Literaturesmentioning

confidence: 99%

Plasma Synthetic Jet Actuators for Active Flow Control

et al. 2018

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The plasma synthetic jet actuator (PSJA), also named as sparkjet actuator, is a special type of zero-net mass flux actuator, driven thermodynamically by pulsed arc/spark discharge. Compared to widely investigated mechanical synthetic jet actuators driven by vibrating diaphragms or oscillating pistons, PSJAs exhibit the unique capability of producing high-velocity (>300 m/s) pulsed jets at high frequency (>5 kHz), thus tailored for high-Reynolds-number high-speed flow control in aerospace engineering. This paper reviews the development of PSJA in the last 15 years, covering the major achievements in the actuator working physics (i.e., characterization in quiescent air) as well as flow control applications (i.e., interaction with external crossflow). Based on the extensive non-dimensional laws obtained in characterization studies, it becomes feasible to design an actuator under several performance constraints, based on first-principles. The peak jet velocity produced by this type of actuator scales approximately with the cubic root of the non-dimensional energy deposition, and the scaling factor is determined by the electro-mechanical efficiency of the actuator (O(0.1%–1%)). To boost the electro-mechanical efficiency, the energy losses in the gas heating phase and thermodynamic cycle process should be minimized by careful design of the discharge circuitry as well as the actuator geometry. Moreover, the limit working frequency of the actuator is set by the Helmholtz natural resonance frequency of the actuator cavity, which can be tuned by the cavity volume, exit orifice area and exit nozzle length. In contrast to the fruitful characterization studies, the application studies of PSJAs have progressed relatively slower, not only due to the inherent difficulties of performing advanced numerical simulations/measurements in high-Reynolds-number high-speed flow, but also related to the complexity of designing a reliable discharge circuit that can feed multiple actuators at high repetition rate. Notwithstanding these limitations, results from existing investigations are already sufficient to demonstrate the authority of plasma synthetic jets in shock wave boundary layer interaction control, jet noise mitigation and airfoil trailing-edge flow separation.

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Section: Institutions Representative Literaturesmentioning

confidence: 99%

Plasma Synthetic Jet Actuators for Active Flow Control

et al. 2018

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“…The recent experimental study showed that the plasma filament created by the ultrashort laser pulse forms a low-density region that interacts with the bow shock [16]. A number of recent numerical studies also confirmed the formation of vorticity on the interaction of low density region and bow shock, that results a modulation of drag coefficient and flow separation in the high speed flows [17][18][19][20][21]. However, dynamics of the formed laser plasma was not modeled in those studies.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of dual-pulse laser energy deposition in a supersonic flow

Mahamud

Hartman

Tropina

2020

J. Phys. D: Appl. Phys.

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Dynamics of plasma generated by the dual-pulse laser in a supersonic flow was studied numerically. The mathematical model includes species, momentum, electronic, vibrational and translational energy equations for the multicomponent ionized air. The model examines temporal dynamics of the formed air plasma and how it affects the drag, pressure signature and vorticity generation in a supersonic flow around a wedge. We observed that nonequilibrium plasmas is more effective in the drag reduction compared with the simultaneous thermal energy addition. The maximum drag reduction of around 50% and the maximum drag coefficient reduction of 30% was attained through the dual-pulse laser energy deposition. Variation of the plasma spot orientation did not significantly influence the drag reduction. We suggested that the surface pressure changes were not controlled by the vorticity generation but occurred due to the density changes and the formation of the low-density plasma spot.

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“…The interaction between the jet and the supersonic mainstream produces complex flow structures, which dominate the mixing process and are the key to understanding the organization of combustion in scramjets. There are many interesting phenomena in the flow fields of JISCs, including turbulent boundary layers, 1 shock wave, 2 separation, 3 and mixing. 4,5 The interference between these phenomena makes the research content more complicated.…”

Section: Introductionmentioning

confidence: 99%

Effects of confinement and curvature on a jet in a supersonic cross-flow

Xiong

Sun

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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To reveal the effects of confinement and curvature on the jet mixing in a supersonic cross-flow, large eddy simulations were conducted to study the jet in supersonic cross-flow in a channel and a pipe at a Mach number of 2.7. The comparison was based on an equal friction Mach number, friction Reynolds number, and Prandtl number. The synthetic eddy model was utilized to generate the inflow turbulent boundary layer. Our study shows the major counter-rotating vortex pair (CVP) was higher in the pipe than in the channel, while the trailing CVP was larger and appeared within the recirculating flow. The pipe had a stronger shock train than the channel due to the confinement and curvature of the pipe. The jet penetration of the pipe is 18.4% larger than that of the channel at x/ D = 10, and the stream velocity of the pipe is much more reduced behind the jet than in the channel. Three reasons for the higher mixing efficiency of the pipe are revealed according to our findings, including the larger and higher major CVP, the higher penetration, the stronger shock. The mixing efficiency of the pipe is 4.68% higher than that of the channel due to the above reasons at x/ D = 10.

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High-frequency counter-flow plasma synthetic jet actuator and its application in suppression of supersonic flow separation

Cited by 38 publications

References 31 publications

Plasma Synthetic Jet Actuators for Active Flow Control

Plasma Synthetic Jet Actuators for Active Flow Control

Dynamics of dual-pulse laser energy deposition in a supersonic flow

Effects of confinement and curvature on a jet in a supersonic cross-flow

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