脉冲表面电弧放电对高超声速压缩拐角的非定常控制机理

doi:10.7527/S1000-6893.2022.27744

Abstract

Abstract:

A large number of experimental results indicate that the pulsed surface arc discharge plasma has a good ability to control the shock position and Shock Wave/Boundary Layer Interaction （SWBLI） in the hypersonic flows. Because of the short discharge time， strong electromagnetic interference and limited discharge area， it is difficult to obtain quantitative experimental data. In most experiments only qualitative Schlieren images were obtained. To reveal the unsteady control mechanism of pulsed surface arc discharge plasma， it is necessary to establish a numerical simulation method for the interactions between the surface arc discharge plasma and the hypersonic flows. In present work， the unsteady control mechanism of pulsed surface arc discharge plasma on hypersonic compression corner flow is studied by using numerical and experimental methods. Based on the theoretical analysis and experimental results， a three-dimensional phenomenological model of the pulsed surface arc discharge is established. Joule-heating generated by arc discharge is added to the energy equation as a spatial power density source term to simulate the interaction between the surface arc discharge plasma and the hypersonic compression corner flow. The numerical Schlieren images at different time were well predicted compared with that of experiment， which verifies the correctness of the phenomenological model. The unsteady numerical results reveal the interaction mechanism between the arc discharge plasma and the double wedge hypersonic flow. The local Joule-heating generated by the surface arc discharge induces the formation of the near-wall separation zone， leading to the increase of the local displacement thickness and the formation of the unsteady virtual wedge moving along the wall. The moving virtual wedge generates an oblique shock wave with varying strength， which was reflected by the front wedge shock wave forming an unsteady shock/shock interaction. The thermal gas bulb generated by arc discharge can effectively regulate the oblique shock wave. In a single pulse discharge， the maximum drag reduction is around 2%， and the maximum pitch moment change is around 3%.

Key words: surface arc discharge, plasma flow control, hypersonic flow, phenomenological model, unsteady control

CLC Number:

V411

Bo DING, Zhenli CHEN, Zihan JIAO, Jincheng WANG, Zheng LI, Guanghui BAI. Unsteady control mechanisms of hypersonic compression corner using pulsed surface arc discharge[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127744-127744.

Figures/Tables 22

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参数	x方向力/ kg	y方向力/ kg	z方向力/ kg	x方向力矩/ （kg∙m）	y方向力矩/ （kg∙m）	z方向力矩/ （kg∙m）
载荷	8	25	12.5	0.6	0.8	1.5
误差	0.1	0.1	0.1	0.14	0.19	0.1

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Unsteady control mechanisms of hypersonic compression corner using pulsed surface arc discharge

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