Reverse jet characteristics of plasma synthetic jet in hypersonic flow field

被引：0

作者：

Ma Z. ^{[1
]}

Luo Z. ^{[1
]}

Zhao A. ^{[2
]}

Zhou Y. ^{[1
]}

Xie W. ^{[1
]}

Liu Q. ^{[1
]}

Zhu Y. ^{[1
]}

Peng W. ^{[1
]}

机构：

[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha

[2] Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷

基金：

中国国家自然科学基金;

关键词：

flow control; hypersonic incoming flow; penetration depth; plasma synthetic jet; reverse jet;

D O I：

10.7527/S1000-6893.2022.27747

中图分类号：

学科分类号：

摘要：

To study the flow field characteristics of the reverse plasma synthetic jet under hypersonic conditions，experimental and numerical studies were carried out. In the hypersonic incoming flow with Mach number 8，the flow field variation of the reverse plasma synthetic jet was analyzed by comparing the schlieren and exciter outlet pressure monitoring results in the experiment and simulation. It is verified that under hypersonic conditions，the outlet pressure oscillation of the reverse plasma synthesis jet actuator is caused by multiple jets generated by multiple backfilling in the cavity，causing multiple shocks to sweep over the actuator outlet. The plasma synthesis jet increases the mass flow of the gas outside the jet area，while the precursor shock propagating upstream merges with the bow shock wave into a single shock. The vortex rings produced under the action of high-momentum jets，the low-pressure regions created by counter-currents，and the high-temperature low-density plasma jets reduce the local Mach number，resulting in an increase in the shock penetration depth. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.

引用

共 33 条

[31] XIE W, LUO Z B, ZHOU Y, Et al., Experimental and numerical investigation on opposing plasma synthetic jet for drag reduction, Chinese Journal of Aeronautics, 35, 8, pp. 75-91, (2022)
[32] QU Z H, ZENG M, LIU W, Et al., Hypersonic aerodynamics, (1999)
[33] XIE W, LUO Z B, HOU L, Et al., Characterization of plasma synthetic jet actuator with Laval-shaped exit and application to drag reduction in supersonic flow, Physics of Fluids, 33, 9, (2021)

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