Effective Mechanisms for Turbulent-separation Control by DBD Plasma Actuator around NACA0015 at Reynolds Number 1,600,000

Sato, Makoto; Asada, Keiichi; Nonomura, Taku; Aono, Hikaru; Yakeno, Aiko; Fujii, Kozo

doi:10.2514/6.2014-2663

Cited by 9 publications

(9 citation statements)

References 45 publications

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“…These suggestions are confirmed by the control of turbulent separation flow at high Reynolds numbers [61]. For the control of the turbulent separation shear layer, only the low burst frequency (F ≈ 1) is effective, since the thickness of the turbulent separation shear layer is larger than the laminar-separation shear layer [61]. The effect of the burst frequency between F 1 and F 6 for various plasma actuator settings is shown in the lower graphs of Fig.…”

Section: Effect Of the Burst Frequencysupporting

confidence: 62%

“…The thickness of the separation shear layer would increase due to the disturbance from the actuator tape, which results in the suppression of the high burst frequency effect. These suggestions are confirmed by the control of turbulent separation flow at high Reynolds numbers [61]. For the control of the turbulent separation shear layer, only the low burst frequency (F ≈ 1) is effective, since the thickness of the turbulent separation shear layer is larger than the laminar-separation shear layer [61].…”

Section: Effect Of the Burst Frequencymentioning

confidence: 52%

“…The present results quantitatively confirm this fact with high accuracy. Moreover, this effective location for the separation control by the plasma actuator was observed even in the turbulent separated flow at high Reynolds numbers [61].…”

Section: A Effects Of the Location And Operating Conditions Of The Pmentioning

confidence: 97%

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Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

et al. 2015

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A substantial number of large-eddy simulations are conducted on separated flow controlled by a dielectric barrier discharge plasma actuator at a Reynolds number of 63,000. In the present paper, the separated flow over a NACA 0015 airfoil at an angle of attack of 12 deg, which is just poststall, is used as the base flow for separation control. The effects of the location and operating conditions of the plasma actuator on the separation control are investigated by a parametric study. The control effect is evaluated based on the improvement of not only the lift coefficient but also the drag coefficient over an airfoil. The most effective location of the plasma actuator for both lift and drag improvement is precisely confirmed to be upstream of the natural separation point. Even a low burst ratio is found to be sufficient to obtain the same improvements as the cases with a high burst ratio. The effective nondimensional burst frequency F is observed at 4 ≤ F ≤ 6 for the improvement in the lift coefficient and at 6 ≤ F ≤ 20 for that in the drag coefficient.The lift/drag ratio shows a clear peak at 6 ≤ F ≤ 10. To clarify the mechanism of the laminar-separation control, the effect of a turbulent transition is investigated. There is a clear relationship between the separation control effect and the turbulent transition at the shear layer. An earlier and smoother transition case shows greater improvements in the lift and drag coefficients. Flow analyses show that the cases with early and smooth turbulent transition can attach the separated flow further upstream, resulting in a higher suction peak of the pressure coefficient. In addition, another mechanism of the separation control is observed in which the lift coefficient is improved, not by the reattachment through the turbulent transition but by the large-scale vortex shedding induced by the actuation. It is possible to separate these two dominant mechanisms based on the effect of the turbulent transition on the separation control. Nomenclature a = speed of sound BR = burst ratio C D = drag coefficientlength scale D c = ratio between electrostatic body force added by plasma actuator and dynamic pressure D c;effe = effective D c value E i = electric field vector induced by plasma actuator e = total energy per unit volume F base = nondimensional base frequency for sine wave of input voltage; f base c∕u ∞ F = nondimensional frequency of burst wave; f c∕u ∞ f = frequency f base = base frequency for sine wave of input voltage f = frequency of burst wave M ∞ = freestream Mach number Pr = Prandtl number p = pressure Q c = electric charge q i = heat flux vector Re = Reynolds number St = Strouhal number S Suzen = body force vector determined from Suzen model S i = body force vector; Q c E i T = burst wave period T base = period of sine wave T off = period when sine wave switch is off during burst wave period T on = period when sine wave switch is on during burst wave period t = time u = velocity in chord direction . Member AIAA. Article in Advance / 1 AIAA JOURNAL Downloaded by U...

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Section: Effect Of the Burst Frequencysupporting

confidence: 62%

Section: Effect Of the Burst Frequencymentioning

confidence: 52%

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Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

et al. 2015

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“…With knowledge of the fundamental characteristics of DBD-PAs and the results of their usage [5][6][7][8][9][10][11][12], a DBD-PA-based flow control was applied to stalled stationary airfoils where massive flow separation occurs. Improvements in the aerodynamic performance of the stalled airfoils have been reported in previous investigations [7,8,[11][12][13][14][15][16][17]. For example, Sato et al [13][14][15] presented the effective operational parameters of DBD-PAs based on the results of more than 200 large-eddy simulations (LES) and the mechanisms of suppression of separated flows from the leading edge of an airfoil under a low Reynolds number (O(10 4 )) condition.…”

Section: Introductionmentioning

confidence: 99%

“…For example, Sato et al [13][14][15] presented the effective operational parameters of DBD-PAs based on the results of more than 200 large-eddy simulations (LES) and the mechanisms of suppression of separated flows from the leading edge of an airfoil under a low Reynolds number (O(10 4 )) condition. Moreover, the suppression of the separated flow from the leading edge of the airfoil using a DBD-PA with burst modulations at a chord-based Reynolds number of 10 5 [15,16] and 10 6 [15,17] was demonstrated based on the results of LES. Recently, Fujii [18] provided a comprehensive review based on previous efforts [13][14][15][16][17] and also presented a further possibility of airfoil-flow control using a DBD-PA-based flow control based on the results of LES and other related experiments.…”

Section: Introductionmentioning

confidence: 99%

Separated Flow Control of Small Horizontal-Axis Wind Turbine Blades Using Dielectric Barrier Discharge Plasma Actuators

Aono

Fukumoto

et al. 2020

Energies

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The flow control over the blades of a small horizontal-axis wind turbine (HAWT) model using a dielectric barrier discharge plasma actuator (DBD-PA) was studied based on large-eddy simulations. The numerical simulations were performed with a high-resolution computational method, and the effects of the DBD-PA on the flow fields around the blades were modeled as a spatial body force distribution. The DBD-PA was installed at the leading edge of the blades, and its impacts on the flow fields and axial torque generation were discussed. The increase in the ratios of the computed, cycle-averaged axial torque reasonably agreed with that of the available experimental data. In addition, the computed results presented a maximum of 19% increase in the cycle-averaged axial torque generation by modulating the operating parameters of the DBD-PA because of the suppression of the leading edge separation when the blade’s effective angles of attack were relatively high. Thus, the suppression of the leading edge separation by flow control can lead to a delay in the breakdown of the tip vortex as a secondary effect.

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The Nanosecond-Pulse Surface Dielectric Barrier Discharge Actuation and Its Applications in External Flow Control

赵¹

2016

IJM

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The nanosecond-pulse surface dielectric barrier discharge actuation is the research hotspot in flow separation control. For the typical NS-DBD actuator used in flow control, the basic characteristics and its current research states are briefly presented in this paper. Also, this paper presents a review of the international research progress in the external flow separation control using NS DBD plasma actuation, and then previews the future development of plasma flow control from the aspects of theoretical investigation and engineering applications.

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Effective Mechanisms for Turbulent-separation Control by DBD Plasma Actuator around NACA0015 at Reynolds Number 1,600,000

Cited by 9 publications

References 45 publications

Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

Separated Flow Control of Small Horizontal-Axis Wind Turbine Blades Using Dielectric Barrier Discharge Plasma Actuators

The Nanosecond-Pulse Surface Dielectric Barrier Discharge Actuation and Its Applications in External Flow Control

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