Characterization of Three-Electrode SparkJet Actuator for Hypersonic Flow Control

Zhou, Yan; Xia, Zhang; Luo, Zhenbing; Wang, Lin; Deng, Xiong; Qing-hu, Zhang; Yang, Shengke

doi:10.2514/1.j057465

Cited by 23 publications

(2 citation statements)

References 27 publications

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“…Huang et al [44] found that a shock-on-shock interaction occurred when the SPJ shock intersected with the shock induced by a 20 • compression ramp in Mach 2 flow. Research by Zhou et al [45,46] proved that SPJ can significantly weaken the ramp shock both in supersonic and hypersonic flow.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

et al. 2020

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The control of a shock wave produced by a ramp (ramp shock) in Ma3 supersonic flow using a two-electrode SparkJet (SPJ) actuator in a single-pulse mode is studied experimentally. Except for schlieren images of the interaction process of SPJ with the flow field, a dynamic pressure measurement method is also used in the analysis of shock wave control. In a typical experimental case, under the control of single-pulsed SPJ, the characteristic of ramp shock changes from “short-term local upstream motion” in the initial stage to “long-term whole downstream motion” in the later stage. The angle and position of the ramp shock changes significantly in the whole control process. In addition, the dynamic pressure measurement result shows that the ramp pressure is reduced by a maximum of 79% compared to that in the base flow field, which indicates that the ramp shock is significantly weakened by SPJ. The effects of some parameters on the control effect of SPJ on the ramp shock are investigated and analyzed in detail. The increase in discharge capacitance helps to improve the control effect of SPJ on the ramp shock. However, the control effect of the SPJ actuator with medium exit diameter is better than that with a too small or too large one. In addition, when the SPJ exit is located in the separation zone and outside, the change in the ramp shock shows significant differences, but the control effect in the case of medium ramp distance is better when the SPJ exit is located outside the separation zone.

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Section: Introductionmentioning

confidence: 99%

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

et al. 2020

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“…They found that the PSJs could significantly enhance the lateral stability of the flying wing model while increasing the lift and decreasing the drag, and the fluctuation range of the rolling moment coefficient was reduced by 66.7%. Zhou et al [16,17] also achieved a good flow control effect in supersonic flow by using a threeelectrode PSJ actuator.…”

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confidence: 99%

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

et al. 2022

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An air-supplement plasma synthetic jet (PSJ) actuator increases the air supplemental volume in the recovery stage and improves the jet energy by attaching a check valve to the chamber of a conventional actuator. To explore the flow control effect and mechanism of the air-supplement actuator, via particle image velocimetry experiments in a low-speed wind tunnel, the flow field and boundary layer characteristics of a two-dimensional airfoil surface under different actuation states were compared for different attack angles and jet orifices. The experimental results show that, compared with the conventional actuation state, the jet energy of the air-supplement PSJ is higher and the indirect mixing effect of the counter-vortex sequence produced by the jet-mainstream interaction is stronger. Furthermore, the boundary layer mixing effect is better, which can further suppress flow separation and improve the critical flow separation attack angle. Moreover, increasing the jet momentum coefficient can enhance the flow control effect. The findings of this study could provide guidance for the flow control application of air-supplement PSJs.

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Vortical structures and density fluctuations analysis of supersonic forward-facing step controlled by self-sustaining dual synthetic jets

et al. 2020

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Characterization of Three-Electrode SparkJet Actuator for Hypersonic Flow Control

Cited by 23 publications

References 27 publications

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

Vortical structures and density fluctuations analysis of supersonic forward-facing step controlled by self-sustaining dual synthetic jets

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