Forebody vortex control with a wire-based DBD plasma actuator

GAO Chao; NI Zhangsong; XUE Ming; ZHENG Borui

doi:10.7638/kqdlxxb-2020.0116

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Forebody vortex control with a wire-based DBD plasma actuator

更新时间：2026-05-28

- Forebody vortex control with a wire-based DBD plasma actuator
- Vol. 39, Issue 2, Pages: 39-52(2021)
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710071
  2. 西安理工大学自动化与信息工程学院,西安,710048
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0116
  CLC： O539
- Published：2021
- 稿件说明：
移动端阅览
高超, 倪章松, 薛明, 郑博睿. 基于新型丝状电极等离子体激励器的前体涡控制[J]. 空气动力学学报, 2021, 39(2): 39-52.

GAO Chao, NI Zhangsong, XUE Ming, et al. Forebody vortex control with a wire-based DBD plasma actuator[J]. 2021, 39(2): 39-52.
高超, 倪章松, 薛明, 郑博睿. 基于新型丝状电极等离子体激励器的前体涡控制[J]. 空气动力学学报, 2021, 39(2): 39-52. DOI： 10.7638/kqdlxxb-2020.0116.

GAO Chao, NI Zhangsong, XUE Ming, et al. Forebody vortex control with a wire-based DBD plasma actuator[J]. 2021, 39(2): 39-52. DOI： 10.7638/kqdlxxb-2020.0116.

摘要

本文首次将新型丝状暴露电极DBD等离子激励器应用于大迎角下细长体非对称涡控制。丝状暴露电极的材料的选择对DBD推力以及推力效率至关重要，通过地面精细推力测量对丝状暴露电极等离子体激励器进行了优化，结果表明，本文研究材料中采用钨丝作为暴露电极，其推力效率最优；且随着电极直径从

= 0.3 mm 减小到

= 0.08 mm，DBD推力效率显著提升。基于优化后的DBD激励器，将其应用于前体非对称涡控制：未施加等离子体控制时，压力测量以及PIV结果均表明细长体背风区流场为明显的非对称涡结构；在等离子体激励下，该非对称涡结构可变为对称甚至反向非对称，且非稳态激励控制能力明显优于稳态激励。研究发现，大迎角下细长体非对称涡控制与背风区原始涡系结构有关，其中包含对称涡系和非对称涡系。本文研究为大迎角下细长体非对称涡控制提供了一种新思路，同时也为丝状暴露电极DBD等离子体激励器的应用提供参考。

Abstract

Forebody vortex control with a novel wire-based DBD (Dielectric Barrier Discharge) plasma actuator is studied by wind tunnel experiments in the present work. The configuration of the wire-based DBD plasma actuator

including the material and diameter of the exposed electrode

is optimized through thrust measurements in quiescent air. The results show that the DBD plasma actuator with a wire-based exposed electrode made from tungsten has the highest thrust efficiency

and with the reduction of the diameter from

= 0.3 mm to

= 0.08 mm

the thrust efficiency can be greatly improved. The optimal configuration of

the wire-based DBD plasma actuator is used for the forebody vortex control through wind tunnel experiments. When the plasma control is not applied

results of the pressure and PIV measurements indicate that the flow field in the leeward zone is a distinct asymmetric vortex structure. Under plasma actuation

the asymmetric vortex structure can be symmetrical or even mirror asymmetric with respect to the case “plasma off”

and the control ability in the burst-mode actuation can be significantly improved compared to the steady operation. It is found that the forebody vortex control effect depends on the vortex structure of “plasma off”

which can be either symmetric or asymmetric. This study presents a new approach for the forebody vortex control with the wire-based DBD plasma actuator

which can further improve the aerodynamic flow control on aircrafts with slender bodies.

关键词

Keywords

references

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