Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil

WANG Rongchao; GAO Yongxin; WANG Zhongming; LI Yiwen; YAO Cheng

doi:10.7638/kqdlxxb-2024.0148

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil

更新时间：2026-05-28

- Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil
- Vol. 43, Issue 8, Pages: 36-49(2025)
- 作者机构：
  
  1. 合肥工业大学土木与水利工程学院,合肥,230009
  2. 空军工程大学等离子体动力学重点实验室,西安,710038
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0148
  CLC： V211.4;P185.3
- Published：2025
- 稿件说明：
移动端阅览
王荣超, 高永新, 汪忠明, 等. 火星条件下DBD激励对NACA 0012翼型气动特性的影响[J]. 空气动力学学报, 2025, 43(8): 36−49.

WANG Rongchao, GAO Yongxin, WANG Zhongming, et al. Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil[J]. 2025, 43(8): 36-49.
王荣超, 高永新, 汪忠明, 等. 火星条件下DBD激励对NACA 0012翼型气动特性的影响[J]. 空气动力学学报, 2025, 43(8): 36−49. DOI： 10.7638/kqdlxxb-2024.0148

WANG Rongchao, GAO Yongxin, WANG Zhongming, et al. Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil[J]. 2025, 43(8): 36-49. DOI： 10.7638/kqdlxxb-2024.0148.

摘要

针对火星大气季节性波动导致的火星无人机翼型升力衰减问题，通过数值模拟方法，在火星低雷诺数、高马赫数条件下研究介质阻挡放电（dielectric barrier discharge，DBD）等离子体激励的作用位置、激励电压及激励频率对NACA 0012翼型升力的影响规律。研究结果表明，翼型上壁面处的DBD激励具有显著的增升效果，且最佳激励位置与攻角密切相关：当攻角为5°时，尾缘处（

= 0.9

）激励效果最佳，可实现106%的升力提升；当攻角增至15°时，前缘处（

= 0.1

）激励效果最好，升力提升幅度达44%。通过提高激励频率和电压参数，可进一步强化DBD激励的增升效果。作用机理分析表明，DBD等离子体激励可有效抑制翼型表面流动分离现象、显著扩大翼型上下表面压力差和改变流场涡量分布，从而提升翼型气动性能。本研究在火星环境参数下定量验证了DBD激励技术对翼型气动性能的提升效果，为火星无人机应对大气波动提供了有效的主动流动控制解决方案。

Abstract

The Martian atmosphere exhibits seasonal fluctuations that result in a reduction in the lift generated by the airfoil of Martian unmanned aerial vehicles (UAVs). This paper investigates the effects of dielectric barrier discharge (DBD) plasma actuation parameters (including actuation location

excitation voltage

and frequency) on the aerodynamic performance of NACA0012 airfoil under low-Reynolds-number and high-Mach-number conditions characteristic of Mars using‌ computational

fluid dynamics (CFD). The results demonstrate that upper-surface DBD actuation significantly enhances airfoil lift

with the optimal actuation position being angle-of-attack dependent: For the 5° angle-of-attack case

trailing-edge actuation (

= 0.9

) achieves the maximum lift enhancement of 106%; while for the 15° case

leading-edge actuation (

= 0.1

) yields a 44% improvement. Increasing excitation frequency and voltage further amplifies the lift augmentation effect. Mechanism analysis reveals that DBD plasma actuation effectively suppresses airfoil surface flow separation

significantly enlarges the pressure difference between upper and lower surfaces

and alters vorticity distribution within the flow field

thereby enhancing airfoil aerodynamic performance. This research quantitatively validates the efficacy of DBD actuation for airfoil performance enhancement under Martian atmospheric conditions

providing a viable active flow control solution for UAVs operating in the variable Martian environment.

关键词

Keywords

references

ZHAO P Y, QUAN Q Q, DENG Z Q, et al. Overview of research on rotary-wing Mars unmanned aerial vehicles[J]. Journal of Astronautics, 2018, 39(2): 121−130 (in Chinese). doi: 10.3873/j.issn.1000-1328.2018.02.002

YANG X G, GAO Y X, WANG Z M, et al. Effect of plasma excitation on aerodynamic characteristics of airfoil on mars[J]. Journal of Beijing University of Aeronautics and Astronautics, 2023, 51(6): 2129−2136 (in Chinese). doi: 10.13700/j.bh.1001-5965.2023.0312

CHAHAT N, MILLER J, DECROSSAS E, et al. The Mars helicopter telecommunication link: Antennas, propagation, and link analysis[J]. IEEE Antennas and Propagation Magazine, 2020, 62(6): 12−22. doi: 10.1109/MAP.2020.2990088

WITHROW S, JOHNSON W, YOUNG L A, et al. Mars science helicopter conceptual design[C]// ASCEND 2020, Virtual Event. AIAA, 2020: AIAA 2020-4029. doi: 10.2514/6.2020-4029

LI Y W, WANG Y T, PANG L, et al. Research progress of plasma/mhd flow control in inlet[J]. Chinese Journal of Theoretical and Applied Mechanics, 2019, 51(2): 311−321 (in Chinese). doi: 10.6052/0459-1879-18-290

YU Y, XU J L, GAN N G. Effects of parameters on continuously working plasma synthetic jet[J]. Engineering Applications of Computational Fluid Mechanics, 2014, 8(1): 55−69. doi: 10.1080/19942060.2014.11015497

LI C, HUANG H X, LUO J L, et al. Mixing of low-momentum fluids over the forebody ramp based on micro-vane vortex generators[J]. Acta Aerodynamica Sinica, 2022, 40(1): 119−128 (in Chinese). doi: 10.7638/kqdlxxb-2021.0402

ZHOU D M, SUN X J. Effects of trailing-edge flaps on the power-extraction performance of flapping airfoils[J]. Acta Aerodynamica Sinica, 2021, 39(5): 7−18 (in Chinese). doi: 10.7638/kqdlxxb-2020.0083

LEE T, SU Y Y. Unsteady airfoil with a harmonically deflected trailing-edge flap[J]. Journal of Fluids and Structures, 2011, 27(8): 1411−1424. doi: 10.1016/j.jfluidstructs.2011.06.008

BLINDE P L, HUMBLE R A, VAN OUDHEUSDEN B W, et al. Effects of micro-ramps on a shock wave/turbulent boundary layer interaction[J]. Shock Waves, 2009, 19(6): 507−520. doi: 10.1007/s00193-009-0231-9

GAO C, JIA Y Y, LIU Q K, et al. Experimental investigation of effect of vortex generators' parameter on aerodynamic performance of thin airfoil[J]. Acta Energiae Solaris Sinica, 2021, 42(5): 364−372 (in Chinese). doi: 10.19912/j.0254-0096.tynxb.2019-0902

SHI Q, LI H. Numerical simulation on action of flow control and wave drag reduction effect with contour bump located on the supercritical airfoil[J]. Acta Aerodynamica Sinica, 2010, 28(4): 462−465 (in Chinese). doi: 10.3969/j.issn.0258-1825.2010.04.018

KIM S D. Aerodynamic design of a supersonic inlet with a parametric bump[J]. Journal of Aircraft, 2009, 46(1): 198−202. doi: 10.2514/1.37416

DUAN H S, LIU P Q, CHEN J Z, et al. Numerical investigation of the suction-laminar-flow-control technology on an airfoil[J]. Acta Aerodynamica Sinica, 2010, 28(6): 676−682 (in Chinese). doi: 10.3969/j.issn.0258-1825.2010.06.011

ZHANG W L, TAN J J, CHEN Z H, et al. Optimization of suction control on separation flow around an airfoil at low Reynolds number[J]. Acta Aerodynamica Sinica, 2015, 33(6): 757−764 (in Chinese). doi: 10.7638/kqdlxxb-2014.0063

MA Z M, ZHANG X. Flow field produced by a plasma synthetic jet actuator[J]. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(7): 1−8 (in Chinese). doi: 10.6052/0459-1879-24-045

DENG X, ZHAO Z J, WANG Q W, et al. Research on longitudinal aerodynamic control characteristics of flying wing based on leading-edge dual synthetic jets[J]. Acta Aerodynamica Sinica, 2022, 40(5): 79−90 (in Chinese). doi: 10.7638/kqdlxxb-2022.0049

ZHAO X H, LI Y H, WU Y, et al. Investigation on the acceleration characteristic by plasma aerodynamic actuation[J]. Acta Aerodynamica Sinica, 2010, 28(2): 168−173,196 (in Chinese). doi: 10.3969/j.issn.0258-1825.2010.02.008

LIU J W, LIU Z T, DING S H, et al. Study on lift enhancement and drag reduction of NACA0012 airfoil under plasma thermal effect[J]. Journal of Propulsion Technology, 2020, 41(5): 1055−1062 (in Chinese). doi: 10.13675/j.cnki.tjjs.190574

GUERRA V, SILVA T, PINHÃO N, et al. Plasmas for in situ resource utilization on Mars: Fuels, life support, and agriculture[J ] . Journal of Applied Physics, 2022, 132(7): 070902. doi: 10.1063/5.0098011

WU Y K, MA X G, FENG L M, et al. Research progress of flow control on shock wave/boundary layer interaction in supersonic inlets[J ] . Chinese journal of applied mechanics, (2024-07-10)[2025-01-09 ] (in Chinese). http://kns.cnki.net/kcms/detail/61.1112.o3.20240708.1140.002.html .

YANG H S, ZHAO G Y, LIANG H, et al. Research progress on influence factors of airfoil dynamic stall and flow control[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(8): 119−144 (in Chinese). doi: 10.7527/S1000-6893.2019.23605

JIN Y Z, ZHENG B R, YU M H, et al. Experimental study on flow control of asymmetric vortex over the leeward region of the head of the slender body by sliding discharge plasma actuation[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(5): 43−51 (in Chinese). doi: 10.11729/syltlx20210101

WANG Y D, LI J, LIANG H, et al. A simulation of improving aerodynamic characteristics of high-lift wing by plasma excitation[J]. Journal of Air Force Engineering University (Natural Science Edition), 2017, 18(6): 1−7 (in Chinese). doi: 10.3969/j.issn.1009-3516.2017.06.001

HUANG G J, DAI Y T, YANG C. Plasma-based flow control on pitching airfoil at low Reynolds number[J]. Chinese Journal of Theoretical and Applied Mechanics, 2021, 53(1): 136−155 (in Chinese). doi: 10.6052/0459-1879-20-183

TAKAGAKI M, ISONO S, NAGAI H, et al. Evaluation of plasma actuator performance in Martian atmosphere for applications to Mars airplanes[C]//Proc of the 4th Flow Control Conference, Seattle, Washington. AIAA, 2008: AIAA 2008-3762. doi: 10.2514/6.2008-3762

ZHOU L W, YANG Z, WEI L Q, et al. Characteristics of a low-pressure carbon-dioxide surface dielectric barrier discharge plasma ion-wind thruster[J]. AIAA Journal, 2023, 61(11): 4828−4838. doi: 10.2514/1.j063049

ZHANG P F, LIU A B, WANG J J. Aerodynamic modification of NACA 0012 airfoil by trailing-edge plasma gurney flap[J]. AIAA Journal, 2009, 47(10): 2467−2474. doi: 10.2514/1.43379

SHYY W, JAYARAMAN B, ANDERSSON A. Modeling of glow discharge-induced fluid dynamics[J]. Journal of Applied Physics, 2002, 92(11): 6434−6443. doi: 10.1063/1.1515103

FARRELL W M, MCLAIN J L, COLLIER M R, et al. Is the electron avalanche process in a Martian dust devil self-quenching?[J]. Icarus, 2015, 254: 333−337. doi: 10.1016/j.icarus.2015.04.003

LIANG H, LI Y H, JIA M, et al. Energy conversion process analysis of plasma aerodynamic actuation[J]. High Voltage Engineering, 2010, 36(12): 3054−3058 (in Chinese). doi: 10.13336/j.1003-6520.hve.2010.12.002

XUE M. Study on vortex structure evolution and flow control under plasma excitation[D]. Xi'an: Northwestern Polytechnical University, 2020 (in Chinese). doi: 10.27406/d.cnki.gxbgu.2020.000386

KONING W J F, ALLAN B G, ROMANDER E A, et al. Comparing 3D and 2D CFD for Mars helicopter ingenuity rotor performance prediction[C]// 49th European Rotorcraft Forum 2023, DE, Bückeburg, September 5, 2023. https://ntrs.nasa.gov/citations/20230012866

HIDAKA H, OKAMOTO M. An experimental study of triangular airfoils for Mars airplane[J]. Transactions of the Japan Society of Aeronautical and Space Sciences, Aerospace Technology Japan, 2014, 12: Pk_21−Pk_27. doi: 10.2322/tastj.12.Pk_21

YANG B, SUN M, BAI M D. Experimental investigation of airfoil flow separation control by dielectric barrier discharge plasma actuator[J]. High Voltage Engineering, 2014, 40(1): 212−218 (in Chinese). doi: 10.13336/j.1003-6520.hve.2014.01.031

LIU R B, ZENG J H, MEI X Y, et al. Experimental research on active control of S-shaped inlets flow separation by AC-DBD plasma[J]. Journal of Propulsion Technology, 2023, 44(10): 43−55 (in Chinese). doi: 10.13675/j.cnki.tjjs.2207044

KELLEY C, BOWLES P, COONEY J, et al. High Mach number leading-edge flow separation control using AC DBD plasma actuators[C]// 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. AIAA, 2012: AIAA 2012-906. doi: 10.2514/6.2012-906

CHEN K, SHI Z W, WEI C Y. Influence of DBD on aerodynamic performance of high lift system[J]. Flight Dynamics, 2020, 38(2): 12−16 (in Chinese). doi: 10.13645/j.cnki.f.d.20191115.008

NIU Z G, ZHAO G Y, LIANG H, et al. A review of vortical flow control over delta wings using DBD plasma actuation[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(3): 33−47 (in Chinese). doi: 10.7527/S1000-6893.2019.22201

WANG L, XIA Z X, LUO Z B, et al. Exp erimental study on the characteristics of a two-electro de plasma synthetic jet actuator[J]. Acta Physica Sinica, 2014, 63(19): 194702 (in Chinese). doi: 10.7498/aps.63.194702

WANG W B, JIANG Y B, HUANG Y, et al. Lift enhancement wind tunnel test with flap blowing for large aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 68−78 (in Chinese). doi: 10.7527/S1000-6893.2022.27870

ZHANG S H, DENG F, QIN N, et al. Numerical study on impact of shock control bump on transonic buffet[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(11): 345−360 (in Chinese). doi: 10.7527/S1000-6893.2022.26806

ZHENG H B, GAO C, WU B, et al. Drag reduction control of turbulent boundary layer based on plasma actuation[J]. Journal of Aerospace Power, 2023, 38(5): 1157−1165 (in Chinese). doi: 10.13224/j.cnki.jasp.20210546

OLASEK K, KARCZEWSKI M. Velocity data-based determination of airfoil characteristics with circulation and fluid momentum change methods, including a control surface size independence test[J]. Experiments in Fluids, 2021, 62(5): 108. doi: 10.1007/s00348-021-03193-9

CHEN F, QUAN X B, SONG Y P. Fundamentals of aerodynamics[M]. Harbin: Harbin Institute of Technology Press, 2015 (in Chinese).

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Aerodynamic optimization design of blended winglets for HALE UAVs

Aerodynamic characteristics of airfoils with Gurney flaps in the Martian atmospheric environment

Numerical investigation on aerodynamic characteristics of dragonfly corrugated airfoils in gliding and flapping flight

Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge

Vorticity transport characteristics of separated shear layer under AC/NS-DBD plasma actuation

Related Author

LUO Yang

WANG Zonghui

BAO Xiaoxiang

ZHAO Jiaxiang

LI Jianbo

ZHANG Chaoqun

CHEN Baiyi

CHEN Sinuo

Related Institution

UAV System Design Department, CH UAV Technology Co., Ltd., Beijing

National Key Laboratory of Helicopter Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing

College of Aerospace Engineering, Nanjing University of Aeronautics And Astronautics, Nanjing

PLA Rocket Force Nco College, Weifang

Low Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

AI问答

⁰