A comparative study of alternating current and nanosecond plasma actuators in flow separation control

Zheng, Jianguo; Cui, Yongdong; Khoo, Boo Cheong

doi:10.1016/j.ijheatmasstransfer.2019.02.030

Cited by 30 publications

(4 citation statements)

References 34 publications

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“…Plasma actuation effectively alleviated the pitch instability of laminar separation flutter at a high Reynolds number of 77,000. Zheng et al [15] analyzed two flow control principles of alternating current (AC) plasma and nanosecond plasma both numerically and experimentally. Results indicated that the wall jet at the AC plasma discharge only affected the fluid flow near the actuator.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

et al. 2022

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Section: Introductionmentioning

confidence: 99%

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

et al. 2022

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“…The flow-control devices such as flaps and slats are used for the prevention of stall; however, they can be problematic because of their heavy weight and poor response time [1]. Recently, dielectric barrier discharge plasma actuators (DBDPAs) have attracted attention as new flow-control devices [2][3][4]. A DBDPA, which is composed of a dielectric sheet sandwiched between two thin electrodes, generates a discharge on the dielectric sheet, thereby achieving flow control.…”

Section: Introductionmentioning

confidence: 99%

Effect of burst ratio on flow separation control using a dielectric barrier discharge plasma actuator at Reynolds number 2.6 × 10⁵

Suzuki¹,

Komuro²,

Nonomura³

et al. 2021

J. Phys. D: Appl. Phys.

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In this study, the effect of the burst ratio (BR) on flow separation control using an alternating-current dielectric barrier discharge plasma actuator (DBDPA) was investigated. The effects of BR on the lift force on the NACA0015 airfoil were quantitatively evaluated by force measurements, and those on the flow field were measured by particle image velocimetry (PIV) and Schlieren visualisation. The force measurements showed that the recovery of the lift force decreased as BR increased, indicating that the flow separation control effect of the DBDPA decreased as BR increased. The PIV measurements showed that the temporal variation in vorticity was smaller at BR = 80% than at BR = 20% and that the vorticity did not change periodically at BR = 100%. Schlieren visualisation showed that DBDPA-induced flow produced a density gradient near the DBDPA electrode; the gradient was periodically observed and was found to be proportional to BR. In contrast, the density gradient in the separated shear layer varied at the end of each burst waveform, and the degree of variation decreased as BR increased. In addition, the root mean square value of the Schlieren signal intensity in the separated shear layer decreased with increasing BR. This result suggests that not only the strength and frequency of the disturbance input of the DBDPA but also the switching timing of the disturbance input are important for producing vorticity and thereby ensuring flow control.

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“…Zheng et al 27 employed a combination of numerical and experimental investigations to determine the differences between AC-DBD and nanosecond-DBD actuators' capabilities for separation control purposes over NACA 0015 airfoil at a ¼ 15 . Their results demonstrated superiority of the AC-DBD actuators at low Reynolds number to nanosecond-DBD.…”

Section: Introductionmentioning

confidence: 99%

Enhancement of a horizontal axis wind turbine airfoil performance using single dielectric barrier discharge plasma actuator

Fadaei

Davari

Sabetghadam

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Wind turbines are of the most promising devices to cut down carbon emissions. However, some phenomena that adversely affect their performance are inevitable. The aim of the present paper is to investigate flow separation prevention exploiting leading edge (LE) single dielectric barrier discharge plasma actuator (SDBD-PA) on an airfoil belonging to a section of a locally developed wind turbine. The numerical results of the surface pressure distribution over the airfoil were compared with the experimental measurements carried out by the authors on the same blade section, and good agreement was found between numerical and experimental data for both plasma-OFF and plasma-ON cases. An in-depth parametric numerical investigation was then carried out to provide a better understanding of the flow behavior affected by the activation of PA over the same airfoil at post stall angle of attacks (AOAs). According to the results, the frequency and voltage of actuation, AOA, and free stream velocity are shown to have strong impacts on separation delay and actuation effectiveness. In Reynolds number of 2.85 × 105, the maximum PA effectiveness takes place at 21° which is approximately 312%, 307%, and 256% corresponding to the PA location of LE, 0.02 chord, and 0.15 chord, respectively. Also, maximum velocity of the domain is increased three times of the free stream velocity on average for three investigated Reynolds numbers at the frequency and voltage of 12 kHz and 12 kV, respectively. Furthermore, the size of the wake area noticeably contracts due to the presence of the SDBD-PA. The results clearly indicate that the lift and drag coefficients as well as the lift-to-drag ratio fit a linear variation pattern with the frequency of actuation. The variation rate of the aforementioned parameters becomes steeper as the peak voltage of actuation increases. Highly nonlinear aerodynamic responses and significant interactions were demonstrated between the investigated parameters.

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A comparative study of alternating current and nanosecond plasma actuators in flow separation control

Cited by 30 publications

References 34 publications

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

Effect of burst ratio on flow separation control using a dielectric barrier discharge plasma actuator at Reynolds number 2.6 × 10⁵

Enhancement of a horizontal axis wind turbine airfoil performance using single dielectric barrier discharge plasma actuator

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A comparative study of alternating current and nanosecond plasma actuators in flow separation control

Cited by 30 publications

References 34 publications

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

Investigation of Flow Control and Cooling Performance Using Comb Plasma Actuators

Effect of burst ratio on flow separation control using a dielectric barrier discharge plasma actuator at Reynolds number 2.6 × 105

Enhancement of a horizontal axis wind turbine airfoil performance using single dielectric barrier discharge plasma actuator

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Product

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Effect of burst ratio on flow separation control using a dielectric barrier discharge plasma actuator at Reynolds number 2.6 × 10⁵