Flow control on a high-lift wing with microsecond pulsed surface dielectric barrier discharge actuator

Wei, Biao; Wu, Yun; Liang, Hua; Su, Zhi; Li, Yinghong

doi:10.1016/j.ast.2019.105584

Cited by 33 publications

(18 citation statements)

References 27 publications

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“…Besides, the actuation characteristics have a certain relationship with the frequency. When the actuation frequency is greater than the optimal frequency, the ow control effect will be worse (Gursul et al 2007 andWei et al 2020).…”

Section: In Uence Of Pulse Frequency On the Ow Control Effectmentioning

confidence: 99%

“…But there are also problems such as low e ciency and limited control range. In recent years, due to simple structure, fast response, large frequency bandwidth, and low energy consumption (Corke et al 2009), surface dielectric barrier discharge (SDBD) has been widely used in airfoil (Little et al 2010), laminar-to-turbulent ow transition control (Joussot et al 2010), wing lift promotion Wei et al 2020) and boundary layer acceleration (Im et al 2010), and many other elds. Under the conditions of chord Reynolds numbers from 10 4 to 10 5 and freestream turbulence levels from 0.08 to 2.85%, SDBD was applied for separation control on the low-pressureturbine blades.…”

Section: Introductionmentioning

confidence: 99%

“…Different from AC-SDBD with limited ow control effects in high subsonic range (Li et al 2006) and nSDBD with high power supply, weight and costs, μSDBD can control the ow separation effectively in a wide range of freestream velocity with lower weight and costs. (Wei et al 2020). The feasibility and e cacy of μSDBD in the ight test with a scaled model of a certain type of amphibious plane were also veri ed (Su et al 2018), which shows the potential of μSDBD in ow separation control on nacelles.…”

Section: Introductionmentioning

confidence: 99%

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Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

Jia

Liang

et al. 2021

Flow Turbulence Combust

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Flow separation under crosswind conditions seriously jeopardizes the quality of the nacelle's ow eld. In this paper, microsecond pulsed surface dielectric barrier discharge (µSDBD) is used to suppress the ow separation and reduce the crosswind distortion of the nacelle. The ow structure induced by the µSDBD is rst explored by a high-speed schlieren system. The pressure waves composed of a cylindrical wave surrounding the electrodes and a at wave at the top of the cylindrical one can be perceived, which indicates the fast gas heating produced by the µSDBD. A set of wind tunnel tests are then conducted to verify the ability of µSDBD to suppress the nacelle ow separation and study the in uence laws of pulse frequency, coverage area, and the actuator layout on the ow control effects. Results show that plasma actuation can not only improve the total pressure at the exit of the nacelle but also suppress the ow distortion caused by the crosswind. The best ow control effect can be achieved at the pulse frequency of 500Hz, with the value of sectional distortion coe cient reduced by 57.76% compared with the baseline condition. The ow control effect with the plasma actuator covering 120° of the nacelle perimeter is better than that of 60° and 180° coverage, showing the highest ow control e ciency in the 120°c ondition. The µSDBD can improve mixing between the boundary layer and the main ow, enhancing the ability of the boundary layer to resist the adverse pressure gradient, which is bene cial to ow separation control.

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Section: In Uence Of Pulse Frequency On the Ow Control Effectmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

Jia

Liang

et al. 2021

Flow Turbulence Combust

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“…Hence, flow control systems are required for overcoming such difficulties. The flow separation control techniques have been considered as a significant field of fluid mechanics [7][8][9][10]. The flow separation control can be achieved employing active methods for example; blowing and suction jets [11][12][13][14], and synthetic jet actuators [15][16][17], or passive methods such as flap, slat, vortex generator, and Gurney flap [18][19][20][21].…”

Section: Introductionmentioning

confidence: 99%

Simultaneous Effect of Suction and Cavity for Controlling Flow Separation on NACA 0012 Airfoil – CFD Approach

Fatahian

2021

Gazi University Journal of Science

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“…The high-lift system determines the takeoff and landing performance of an aircraft and significantly affects its safety, comfort, and environmental friendliness (Wang et al, 2008;Wei et al, 2020). The trailing-edge flap is used to generate the extra lift, and Fowler flaps have been widely used in mainstream civil aircraft because of their good lift increment and reliability.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on technical and conceptual improvements to a civil aircraft trailing-edge flap using passive/active flow control

Wang

Zhang

2021

Engineering Applications of Computational Fluid Mechanics

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Future civil aircrafts require simple, low-noise, and highly efficient trailing-edge flaps. In this study, a detailed numerical study for flap improvements using steady and unsteady Reynolds-averaged Navier-Stokes computations was conducted. A movable trailing edge (MTE) was applied to the main element as a passive flow control method to improve the traditional Fowler flap. A new concept of a backward seamless flap (BSLF) based on the MTE configuration is proposed, which can eliminate external fairings, simplify the mechanisms, and reduce the cruise drag. Then, a wall jet active flow control method was used to improve the BSLF. The improvement effect, flow mechanism, and parameter influences were investigated in detail. The results indicated that the MTE can increase the lift coefficient in the linear segment by 1.2-1.4 for an aerofoil and 0.79 for a wing by controlling the slot flow, energy distribution, and circulation. Moreover, the BSLF provided an improvement in performance higher than 27% over the plain flap, and the wall jet controlled BSLF configuration could reach or even exceed the MTE configuration in terms of performance. The zero-mass jet had a higher control effect and efficiency than the continuous jet. This study highlighted the significance and engineering value for technical improvement and concept exploration of new-generation high-lift devices.

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Flow control on a high-lift wing with microsecond pulsed surface dielectric barrier discharge actuator

Cited by 33 publications

References 27 publications

Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

Simultaneous Effect of Suction and Cavity for Controlling Flow Separation on NACA 0012 Airfoil – CFD Approach

Numerical study on technical and conceptual improvements to a civil aircraft trailing-edge flap using passive/active flow control

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