Vortex dynamics over an airfoil controlled by a nanosecond pulse discharge plasma actuator at low wind speed

Hai DU (杜海); LeiWANG (王磊); Wenjie KONG (孔文杰); Zhiwei SHI (史志伟); Keming CHENG (程克明); Zheng LI (李铮)

doi:10.1088/2058-6272/ab43f5

Plasma Science and Technology > 2019 > 21(12): 125503. > DOI: 10.1088/2058-6272/ab43f5

Hai DU (杜海), LeiWANG (王磊), Wenjie KONG (孔文杰), Zhiwei SHI (史志伟), Keming CHENG (程克明), Zheng LI (李铮). Vortex dynamics over an airfoil controlled by a nanosecond pulse discharge plasma actuator at low wind speed[J]. Plasma Science and Technology, 2019, 21(12): 125503. DOI: 10.1088/2058-6272/ab43f5

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Vortex dynamics over an airfoil controlled by a nanosecond pulse discharge plasma actuator at low wind speed

¹ School of Energy and Power Engineering, Xihua University, Chengdu 610039, People's Republic of China
² Key Laboratory of Fluid and Power Machinery, Ministry of Education, Xihua University, Chengdu 610039, People's Republic of China
³ College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, People's Republic of China

Funds: This work was supported by National Natural Science Foundation of China (No. 51806181), the Open Research Subject of the Key Laboratory (Research Base) of Fluid and Power Machinery (Xihua University), Ministry of Education (szjj2017-086), the Key Scientific Research Fund of Xihua University (No. Z17111)), the financial support of the Sichuan Provincial Department of Education (No. 18ZA0458), the Key Laboratory of Aeroengine Pneumatic and Thermal Defense Science and Technology (No. 6142702180101) and the ‘Young Scholars’ Program of Xihua University.

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Received Date: June 05, 2019
Revised Date: September 09, 2019
Accepted Date: September 11, 2019

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Abstract

Abstract

The vortex dynamics of flow over an airfoil controlled by a nanosecond pulse dielectric-barrierdischarge (NS-DBD) actuator is studied at a Reynolds number of 1×10⁵ through wind tunnel experiments and numerical simulation. The numerical method is validated through comparison of the simulated and measured results regarding the effect of the discharge of an NS-DBD actuator placed on a flat plate. The simulated results show that vorticity is mainly induced by the baroclinic torque after plasma discharge, i.e. the term in the equation of vorticity evolution. Both experimental and simulated results demonstrate that after the discharge of the NS-DBD actuator a series of vortices are developed in the shear layer and pull the high-moment fluid down to the wall, enhancing the mixing of internal and external flows.
- plasma,
- actuator,
- flow control,
- Joule heating,
- vortex

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References (33)

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Vortex dynamics over an airfoil controlled by a nanosecond pulse discharge plasma actuator at low wind speed