Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

Zheng LI (李铮); Zhiwei SHI (史志伟); Hai DU (杜海); Qijie SUN (孙琪杰); Chenyao WEI (魏晨瑶); Xi GENG (耿玺)

doi:10.1088/2058-6272/aacaf0

Plasma Science and Technology > 2018 > 20(11): 115504. > DOI: 10.1088/2058-6272/aacaf0

Zheng LI (李铮), Zhiwei SHI (史志伟), Hai DU (杜海), Qijie SUN (孙琪杰), Chenyao WEI (魏晨瑶), Xi GENG (耿玺). Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing[J]. Plasma Science and Technology, 2018, 20(11): 115504. DOI: 10.1088/2058-6272/aacaf0

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Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

¹ College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, People’s Republic of China
² The Key Laboratory of Fluid and Power Machinery, Xihua University, Chengdu 610039, People’s Republic of China

Funds: This work was supported by Funding of Jiangsu Innovation Program for Graduate Education (No. KYLX16_0310) and the Fundamental Research Funds for the Central Universities (No. NP2016406). This work was also supported by Graduate Innovation Center in NUAA (No. kfjj20170117). The authors would also like to thank China Postdoctoral Science Foun- dation (No. 2017M610325).

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Received Date: December 14, 2017

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Abstract

Abstract

Abstract Dielectric barrier discharge (DBD) plasma is one of most promising flow control method for its several advantages. The present work investigates the control authority of nanosecond pulse DBD plasma actuators on a flying wing model’s aerodynamic characteristics. The aerodynamic forces and moments are studied by means of experiment and numerical simulation. The numerical simulation results are in good agreement with experiment results. Both results indicate that the NS-DBD plasma actuators have negligible effect on aerodynamic forces and moment at the angles of attack smaller than 16°. However, significant changes can be achieved with actuation when the model’s angle of attack is larger than 16° where the flow separation occurs. The spatial flow field structure results from numerical simulation suggest that the volumetric heat produced by NS-DBD plasma actuator changes the local temperature and density and induces several vortex structures, which strengthen the mixing of the shear layer with the main flow and delay separation or even reattach the separated flow.
- nanosecond,
- dielectric barrier discharge,
- flying wing aircraft,
- flow separation control

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References (27)

References

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2.	Shen, Y.-C., Niu, Y.-F., Kong, D.-F. et al. Development and Performance Test of a Seya-Namioka Vacuum Ultraviolet Spectroscopy System \| [Seya-Namioka 类型真空紫外光谱系统的研制和性能测试]. Guang Pu Xue Yu Guang Pu Fen Xi/Spectroscopy and Spectral Analysis, 2024, 44(8): 2158-2165. DOI:10.3964/j.issn.1000-0593(2024)08-2158-08
3.	Tan, M., Ye, Y., Kong, D. et al. Design and operation of a repetitive compact torus injector for the EAST tokamak. Fusion Engineering and Design, 2024. DOI:10.1016/j.fusengdes.2024.114559
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Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing