Drag reduction mechanism using plasma synthetic jet in high-speed flow

被引：0
|
作者：
Gao S. [1 ]
Ding B. [2 ]
Xie X. [3 ]
Li Z. [1 ]
Chen L. [1 ]
Qian S. [1 ]
Jiao Z. [1 ]
Bai G. [1 ]
机构：
[1] Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing
[2] School of Aeronautics, Northwestern Polytechnical University, Xi’an
[3] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷
关键词：
drag reduction; flow control; high-speed flow; plasma; wind tunnel test;
D O I：
10.7527/S1000-6893.2023.29373
中图分类号：
学科分类号：
摘要：
The influence of the plasma synthetic jet on the drag reduction characteristics of the blunt body model in high-speed complex flow fields is investigated experimentally and numerically. The dynamic axial force measurement test of the blunt body with a plasma synthetic jet actuator is carried out in Mach number 8 flow field. The mechanism of penetration model on drag reduction of the blunt body by the plasma synthetic jet is studied. A numerical simulation method suitable for the coupling of plasma active actuation and high-speed flow is established. The wind tunnel test results show that the plasma synthetic jet reduces the drag of the blunt body model by 2. 51 N. The numerical simulation results show that the plasma synthetic jet reduces the drag of the blunt body model by 2. 03 N，and the relative experimental error of drag reduction is 19. 1%. © 2023 Chinese Society of Astronautics. All rights reserved.
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