Turbulent Boundary Layer Separation Control Using Plasma Actuators

Schatzman, David; Thomas, Flint O.

doi:10.2514/6.2008-4199

Cited by 21 publications

(14 citation statements)

References 7 publications

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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.…”

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

et al. 2009

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“…One of the first applications of PSVGs for aerodynamic flow control was reported by Huang et al [5] where plasma-induced streamwise vorticity was used for aeroacoustic control of a low-speed cavity resonance. More recently, Schatzman and Thomas [6] utilized PSVGs to eliminate separation of an adverse pressure gradient turbulent boundary developing on a convex ramp. PSVGs were also found to be quite effective in eliminating unsteady vortex shedding from a circular cylinder in cross flow at high subcritical Reynolds number by Kozlov and Thomas [7] and in a tandem cylinder flow configuration Kozlov and Thomas [8].…”

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confidence: 99%

A Parametric Investigation of Plasma Streamwise Vortex Generator Performance

Wicks

Thomas

Schatzman

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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In this paper a parametric investigation of arrays of plasma streamwise vortex generators (PSVG) is presented. The arrays are flush mounted to a flat plate on which a nominally zero pressure gradient turbulent boundary layer develops upstream of the array. The investigation is focused on characterization of the influence of freestream velocity, applied voltage, length of the covered electrode and spanwise inter-electrode spacing on actuator performance. The metrics used to assess performance are measured spanwise wall normal component mean velocity gradient, ∂V / ∂z , and spanwise longitudinal mean velocity gradient, ∂U / ∂z , downstream of the array. The former quantity is related to direct streamwise vorticity production and the latter is related to spanwise vorticity redistribution to the streamwise component through the term ω z ∂U / ∂z . In addition, a direct comparison is made between the PSVG and passive vortex generators under identical flow conditions. Results demonstrate the ability of the PSVG to harvest energy from the external flow in a manner very similar to the passive VG. This unique feature of PSVG may be exploited for flow control applications. Nomenclature U p = plasma induced jet velocity U ∞ = freestream velocity U = Spanwise cycle-average mean velocity L = covered electrode length λ = spanwise inter-electrode spacing E pp = peak-to-peak excitation voltage U = streamwise mean velocity component V = wall normal mean velocity component x, y, z = streamwise, wall-normal and spanwise spatial coordinates, respectively. ∂U / ∂z = spanwise spatial derivative of streamwise mean velocity ∂V / ∂z = spanwise spatial derivative of wall-normal mean velocity ω x = streamwise component mean vorticity δ = 99% boundary layer thickness δ * = boundary layer displacement thickness Γ x ( ) = circulation Re x = Reynolds number

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“…It can increase lift, reduce resistance, shock absorption and noise reduction [2,3], so it has a wide application prospect in the field of Aeronautics and Astronautics [4]. Also plasma flow control technology has no moving parts, short response time, excitation frequency bandwidth and other excellent features [5,6].The experimental excitation power supply is mainly based on AC power supply and nanosecond power supply, AC power supply provides sinusoidal alternating current, and the direction of the voltage varies periodically with time. The AC-DC power supply adds DC component to the AC power supply, the magnitude of the DC voltage is peak value of the alternating current and the direction is negative, so that the sinusoidal voltage of the AC output moves downward to a peak value, the output voltage of the power supply is in one direction.…”

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Influence of SDBD plasma aerodynamic actuation on flow control by AC power supply and AC-DC power supply

Gao

Hao

2018

IOP Conf. Ser.: Earth Environ. Sci.

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Abstract. In this paper, the excitation effect of single dielectric barrier discharge plasma actuator (SDBD) is compared by using AC power supply and AC-DC power supply. AC-DC power supply is based on the AC power supply, just adding DC component. The flow measurement is carried out by PIV technique. Results show that the excitation effect of AC power supply and AC-DC power supply increases by the increase of voltage, the range of speed field excited by AC power is greater than that of AC-DC power supply. For x direction maximum speed, excited by AC power supply is close to AC-DC, and for y direction maximum speed, AC power supply is greater than AC-DC power supply. So the excitation effect of AC power supply is better than that of AC-DC power supply for SDBD. IntroductionPlasma flow control technology which is a new active control technology has become the focus of current research that can control flow separation effectively [1]. It can increase lift, reduce resistance, shock absorption and noise reduction [2,3], so it has a wide application prospect in the field of Aeronautics and Astronautics [4]. Also plasma flow control technology has no moving parts, short response time, excitation frequency bandwidth and other excellent features [5,6].The experimental excitation power supply is mainly based on AC power supply and nanosecond power supply, AC power supply provides sinusoidal alternating current, and the direction of the voltage varies periodically with time. The AC-DC power supply adds DC component to the AC power supply, the magnitude of the DC voltage is peak value of the alternating current and the direction is negative, so that the sinusoidal voltage of the AC output moves downward to a peak value, the output voltage of the power supply is in one direction. For the same SDBD plasma actuator, when the peak voltage of the AC power supply is same with the AC-DC power supply and the output frequency is the optimum frequency, then the excitation effect of the two power supplies is comparable. The flow field measurement is carried out by PIV technology. The experiment can find that in a certain range, the excitation effect of AC power supply and AC-DC power supply increases with the increase of voltage. At the same voltage, the excitation effect of AC power supply is better than AC-DC power supply.

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Turbulent Boundary Layer Separation Control Using Plasma Actuators

Cited by 21 publications

References 7 publications

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

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

A Parametric Investigation of Plasma Streamwise Vortex Generator Performance

Influence of SDBD plasma aerodynamic actuation on flow control by AC power supply and AC-DC power supply

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