Characterization of the Ionic Wind Induced by a Sine DBD Actuator Used for Laminar-to-Turbulent Transition Delay

Boucinha, Vincent; Magnier, Pierre; Weber, Régine; Joussot, Romain; Dong, Binjie; Hong, Dunpin

doi:10.2514/6.2008-4210

Cited by 26 publications

(24 citation statements)

References 19 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%

“…Such input signal is widely used in literature to control airflow and/or give better insights on the force production process. The upper limit of the driven frequency is numerically of about 100 kHz [27], but transmission of the excitation frequency to the surrounding airflow has been verified from 500 Hz up to 1500 Hz [5,[23][24]. This basic input A sample of the electric wind time-history is plotted in figure 5a for a DBD supplied by a sine wave at f AC =150 Hz (at x=3 mm and y =1 mm, see figure 1 for the coordinate system).…”

Section: Simple Frequency Excitation: Sine Input Signalmentioning

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: Simple Frequency Excitation: Sine Input Signalmentioning

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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“…24,25 Although the pulse mode has been verified to be equally or in some cases more effective than continuous operation, 18,24 plasma actuators under pulse operation and the resulting flowfield have yet to receive detailed investigation as a stand alone phenomenon. A limited number of studies [26][27][28] have been published on the subject. The aim of this paper is to further investigate the behavior of the plasma actuator and the response of the surrounding flow under pulse operation.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on dielectric barrier discharge actuators operating in pulse mode

Kotsonis

Veldhuis

2010

Journal of Applied Physics

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An experimental investigation is performed on the operation of dielectric barrier discharge plasma actuators used as manipulators of secondary and unsteady flow structures such as boundary layer instabilities or shedding vortices. The actuators are tested mainly in pulse mode. High sample rate hot-wire measurements of the induced velocity field downstream of the actuator are taken for the cases of pulse actuation in still air as well as in a laminar boundary layer. Complementary voltage and current measurements are taken to calculate power consumption. Additionally, a study on the influence of the pulse frequency and duty cycle of actuation is performed. Results show the effectiveness of plasma actuators in inducing fluctuating components of velocity when operated in pulse mode. Spectral analysis reveals the connection between the actuator driving signal and the induced flowfield. The magnitude as well as the consistency of the resulting fluctuating field are dependent on both the duty cycle and the pulse frequency. An empirical operational envelope based on phenomenological observations is proposed, for the use of the actuators at specific flow and operational conditions given in the paper.

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“…The plasma discharges were obtained with steady operation, by applying a 1 kHz, 11 kV peak-to-peak sinusoidal voltage signal between the electrodes, using a 30/20A Trek amplifier. With such electrical parameters, the ionic wind maximal velocity is around 3 m/s as measured in Boucinha et al 17 .…”

Section: Actuator Arrangementsmentioning

confidence: 95%

Experimental studies of DBD actuator effects on wing tip vortex topology

Leroy

Molton²,

Carpels³

et al. 2012

6th AIAA Flow Control Conference

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Experiments studying the wing tip vortex, generated by a rectangular wing with a symmetric airfoil section and a straight tip, manipulated by surface plasma actuators are presented in this paper. Objectives are focused on modifying vortex development to alter streamwise vorticity downstream of the wing trailing edge. Actual limitation of the ionic wind magnitude obtained with DBD actuators leads to investigate vortex control by action on the transverse component of the freestream flow velocity. Different DBD arrangements installed near the wing tip were tested to examine effects of momentum addition, firstly on the pressure and suction side surfaces, and secondly, simultaneously located more precisely on the main vortex separation and attachment lines. Stereoscopic PIV measurements were performed in different planes orthogonal to the vortex development axis to visualize and characterize wing tip vortices. According to DBD arrangements, results of the actuation show a slight displacement of the wing tip vortex and a reduction of the mean streamwise vorticity level in its core. Nomenclature c = chord U 0 = freestream velocity X = chord axis Y = transverse axis Z = vertical axis U = chord axis velocity V = transverse axis velocity W = vertical axis velocity k = turbulent kinetic energy  x = streamwise vorticity

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Characterization of the Ionic Wind Induced by a Sine DBD Actuator Used for Laminar-to-Turbulent Transition Delay

Cited by 26 publications

References 19 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

Experimental study on dielectric barrier discharge actuators operating in pulse mode

Experimental studies of DBD actuator effects on wing tip vortex topology

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