Effect of the streamwise pulsed arc discharge array on shock wave/boundary layer interaction control

Tang, Mengxiao; Wu, Yun; Guo, Shu-Guang; Sun, Zhengzhong; Luo, Zhenbing

doi:10.1063/5.0011040

Cited by 41 publications

(7 citation statements)

References 27 publications

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“…Recently, Xie et al [ 11 ] used SparkJet actuator for the first time to achieve an effective control on Endey VI SSI over a double wedge in Mach 6.9 high‐enthalpy hypersonic flow, but the repeat frequency is only 1 Hz. Among the current active flow control methods, surface arc plasma actuation has shown excellent control effects in supersonic shock regulation, [ 12 ] shock/boundary layer interaction, [ 13,14 ] and supersonic boundary layer transition. [ 15 ] Besides, Wang et al [ 16 ] experimentally verified the control ability of the surface arc plasma actuation on Mach 6 hypersonic oblique shock over a ramp.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on shock‐shock interaction over double wedge controlled by surface arc plasma array

Kong

et al. 2022

Contributions to Plasma Physics

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The Mach 8 hypersonic shock-shock interaction (SSI) over a double wedge controlled by the improved high-energy surface arc discharge array (H-SADA) have been investigated with high-speed schlieren imaging. The H-SADA with 10 actuators is installed on the first wedge to deposit energy into the hypersonic flow.In the hypersonic double wedge flow, the arrays of blast wave and thermal bubble induced by H-SADA successively develop into a bump virtual profile and a wedge virtual profile, and the former makes complex SSI structure evolve into a bow shock, the latter makes it evolve into an oblique shock. Under the control of single discharge pulse, the disappearance process and the reconstruction process of SSI structure occur successively, and the whole process lasts for 0.2 ms.The H-SADA works stably at frequency of 500 Hz in hypersonic flow, and there is little difference in the control process of each pulse, which means that the SSI structure disappears for 0.2 ms every 2 ms.

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Section: Introductionmentioning

confidence: 99%

Experimental study on shock‐shock interaction over double wedge controlled by surface arc plasma array

Kong

et al. 2022

Contributions to Plasma Physics

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“…In recent years, arrayed pulsed energy depositions based on nanosecond/microsecond pulsed discharges have been attempted for high-speed flow controls [19,20], which are considered potential approaches to improve supersonic flow qualities. They can induce consistently heated gases that propagate downstream and are gradually expanding during their propagation.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Cai

Gao

Wang

et al. 2022

International Journal of Aerospace Engineering

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This paper proposes a method to improve the mixing efficiency of a supersonic combustor by using arrayed pulsed energy depositions, and this method is verified by a numerical simulation. In the simulation, the Navier-Stokes equations with an energy source are solved to simulate the effects of energy depositions in various distributions on the fuel mixture in the combustor. It is found that the energy deposition arranged in the streamwise direction leads to a significant improvement in the mixing efficiency and maximum concentration decay rate of the ethylene fuel by increasing the scale of the jet-induced counter-rotating vortex pair. The energy deposition arranged in the spanwise direction introduces another counter-rotating vortex pair which can also contribute to the fuel mixture. By comparison, the energy deposition distributed in the streamwise direction and downstream of the jet orifice is shown to be the most effective case in the fuel mixing enhancement. Under the energy deposition, the wall pressure on the trailing edge of the cavity is increased which leads to a decrease in the total pressure recovery of the combustor, but this decrease is not significant.

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“…In addition to the tendency to use NS-DBD plasma actuators in supersonic flow control, array-type plasma actuators have become a research hotspot in SWBLI control during the last decade [28][29][30]. The array-type excitation consists of arc plasma actuators which are focused on the spot localized heating.…”

Section: Introductionmentioning

confidence: 99%

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Shahrbabaki

Bazazzadeh

Khoshkhoo

2021

International Journal of Aerospace Engineering

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In this paper, the effects of streamwise Nanosecond Dielectric Barrier Discharge (NS-DBD) actuators on Shock Wave/Boundary Layer Interaction (SWBLI) are investigated in a Mach 2.5 supersonic flow. In this regard, the numerical investigation of NS-DBD plasma actuator effects on unsteady supersonic flow passing a 14° shock wave generator is performed using simulation of Navier-Stokes equations for 3D-flow, unsteady, compressible, and k ‐ ω SST turbulent model. In order to evaluate plasma discharge capabilities, the effects of plasma discharge length on the flow behavior are studied by investigating the flow friction factor, the region of separation bubble formation, velocity, and temperature distribution fields in the SWBLI region. The numerical results showed that plasma discharge increased the temperature of the discharge region and boundary layer temperature in the vicinity of flow separation and consequently reduced the Mach number in the plasma discharge region. Plasma excitation to the separation bubbles shifted the separation region to the upstream around 6 mm, increased SWBLI height, and increased the angle of the separation shock wave. Besides, the investigations on the variations of pressure recovery coefficient illustrated that plasma discharge to the separation bubbles had no impressive effect and decreased pressure recovery coefficient. The numerical results showed that although the NS-DBD plasma actuator was not effective in reducing the separation area in SWBLI, they were capable of shifting the separation shock position upstream. This feature can be used to modify the structure of the shock wave in supersonic intakes in off-design conditions.

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Effect of the streamwise pulsed arc discharge array on shock wave/boundary layer interaction control

Cited by 41 publications

References 27 publications

Experimental study on shock‐shock interaction over double wedge controlled by surface arc plasma array

Experimental study on shock‐shock interaction over double wedge controlled by surface arc plasma array

Numerical Study on Effects of Arrayed Pulsed Energy Depositions on a Supersonic Combustor

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

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