Airflow Reattachment Along a NACA 0015 Airfoil by Surfaces Dielectric Barrier Discharge Actuator: Time-Resolved Particle Image Velocimetry Investigation

Bénard, Nicolas; Braud, P.; Jolibois, J.; Moreau, Éric

doi:10.2514/6.2008-4202

Cited by 30 publications

(27 citation statements)

References 25 publications

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“…To ease the seeding, the actuator is placed in an airtight glass box whose dimensions are sufficient to limit the wall effects on velocity measurements (300 x 400 x 800 mm 3 ). The sampling frequency varies in [14][15][16][17][18][19][20][21][22][23][24] kHz range and 800,000 bursts are stored for each acquisition points. A slotting method including a weight scheme is coded to post-process the stochastic signal issuing from the LDV system [26].…”

Section: Methodsmentioning

confidence: 99%

“…Another example is the use of non-thermal plasma discharge to excite instability modes of axisymmetric jet flow [20]. Effective flow separation control by plasma seems also involved action on the instability mechanisms originating at the separation point [11][12][21][22]. In most of the studies related to unsteady actuation by plasma discharge, the local jet flow resulting from such operating conditions is not detailed.…”

Section: Introductionmentioning

confidence: 99%

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Capabilities of the dielectric barrier discharge plasma actuator for multi-frequency excitations

Bénard¹,

Moreau²

2010

J. Phys. D: Appl. Phys.

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Abstract:The natural instability mechanisms are inherent in most of the laminar and turbulent flow configurations. Usually, these instabilities result in the formation of flow structures occurring at diverse spatial and time scales. An effective control requires an actuator able to bring momentum transfer over a wide range of frequency to act on these instabilities. Promising results are expected for such control strategy because, according to stability theory, a small amplitude perturbation can be large enough to produce significant effects even at high Reynolds number. Moreover, simultaneous production of small perturbations at several frequencies can enhance or cancel non linear interactions; this opens alternative methods for flow control. The focus of the present study is to demonstrate the ability of plasma actuators to introduce flow perturbations at single and dual frequencies by simply adjusting the waveform of the voltage applied to the plasma actuator. The flows produced by a dielectric barrier discharge supplied by burst, superposition and ring modulations are described in temporal and frequential domains. The results confirm the potential of non-thermal plasma actuators to produce highly unsteady flows at single, double or multiple frequencies.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Capabilities of the dielectric barrier discharge plasma actuator for multi-frequency excitations

Bénard¹,

Moreau²

2010

J. Phys. D: Appl. Phys.

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“…For their inclined flat plate, they employed a wavelet algorithm to detect large-scale vortices in time-resolved particle image velocimetry (PIV) data, which revealed an interesting coalescence of smaller vortices produced near the actuator into one large coherent vortex advecting down the plate per cycle of actuation, in the case of f + = 1 (St = 0.23), and into two coherent vortices per cycle of actuation when f + = 0.5, both of which imply vortex shedding at St = 0.23. A similar configuration (with a dielectric-barrier discharge actuator) was studied by Greenblatt et al [27] (flat plate) and Benard et al [28] (NACA0015). For the flat plate at a = 20 • , 0.3 < f + < 0.6 provided the best lift enhancement, whereas f + > 3 was ineffective, and smoke visualization at f + = 0.4 showed a strong vortex advecting downstream along the chord; f + = 1.5 was optimal for a NACA0015 at a = 16 • .…”

Section: (B) Actuated Flowsmentioning

confidence: 99%

Control of vortex shedding on two- and three-dimensional aerofoils

Colonius

Williams

2011

Phil. Trans. R. Soc. A.

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We review and expand on the control of separated flows over flat plates and aerofoils at low Reynolds numbers associated with micro air vehicles. Experimental observations of the steady-state and transient lift response to actuation, and its dependence on the actuator, aerofoil geometry and flow conditions, are discussed and an attempt is made to unify them in terms of their excitation of periodic and transient vortex shedding. We also examine strategies for closed-loop flow and flight control using actuation of leading-edge vortices.

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“…Introduction T HERE is currently considerable interest in the use of single dielectric barrier discharge (SDBD) plasma actuators for aerodynamic flow control. The diverse applications are too numerous to list here but include, for example, active airfoil leading edge separation control [1,2], control of airfoil dynamic stall [3], bluff body flow control [4][5][6][7][8], boundary layer flow control [9][10][11], highlift applications [12], and turbomachinery flow control [13][14][15], to name just a few. The physics surrounding the operation of SDBD plasma actuators has been the focus of several studies [16][17][18][19] and the mechanism of actuation is now fairly well understood.…”

mentioning

confidence: 99%

Optimization of Dielectric Barrier Discharge Plasma Actuators for Active Aerodynamic Flow Control

et al. 2009

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This paper presents the results of a parametric experimental investigation aimed at optimizing the body force produced by single dielectric barrier discharge plasma actuators used for aerodynamic flow control. A primary goal of the study is the improvement of actuator authority for flow control applications at higher Reynolds number than previously possible. The study examines the effects of dielectric material and thickness, applied voltage amplitude and frequency, voltage waveform, exposed electrode geometry, covered electrode width, and multiple actuator arrays. The metric used to evaluate the performance of the actuator in each case is the measured actuator-induced thrust which is proportional to the total body force. It is demonstrated that actuators constructed with thick dielectric material of low dielectric constant produce a body force that is an order of magnitude larger than that obtained by the Kapton-based actuators used in many previous plasma flow control studies. These actuators allow operation at much higher applied voltages without the formation of discrete streamers which lead to body force saturation.Nomenclature b = electrode serration width E = electric field f = body force Gr = Grashof number h = electrode serration height Re = Reynolds number T = actuator-induced thrust U j = wall jet velocity V pp = peak-to-peak voltage V rms = root-mean-square voltage x = streamwise spatial coordinate y = wall-normal spatial coordinate " = dielectric constant = fluid density c = charge density

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Airflow Reattachment Along a NACA 0015 Airfoil by Surfaces Dielectric Barrier Discharge Actuator: Time-Resolved Particle Image Velocimetry Investigation

Cited by 30 publications

References 25 publications

Capabilities of the dielectric barrier discharge plasma actuator for multi-frequency excitations

Capabilities of the dielectric barrier discharge plasma actuator for multi-frequency excitations

Control of vortex shedding on two- and three-dimensional aerofoils

Optimization of Dielectric Barrier Discharge Plasma Actuators for Active Aerodynamic Flow Control

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