Pulsed Discharge Actuators for Rectangular Wing Separation Control

Sidorenko, A. A.; Zanin, B. Yu.; Postnikov, B. V.; Budovsky, A. D.; Starikovskii, Andrei; Roupassov, Dmitry; Zavialov, Ivan; Malmuth, N.; Smereczniak, P.; Silkey, Joseph

doi:10.2514/6.2007-941

Cited by 65 publications

(35 citation statements)

References 4 publications

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“…The presented velocity distributions point to a pressing of the boundary layer to the surface near which the dielectric barrier discharge forms a plasma layer, which agrees with the results obtained in [8]. The use of the dielectric barrier discharge plasma permits also solving the problem of gas flow separation from the surface of the wing [9]. The authors of [10] managed to prevent gas flow separation at an angle of attack of 5 o for velocities of up to 2.85 m ⁄ s, and with increasing angle of attack to 15-21 o for velocities of up to 75 m ⁄ s.…”

supporting

confidence: 88%

Influence of the barrier discharge on the aerodynamic drag of the Zhukovskii airfoil under various air flow conditions

Khramtsov

Penyazkov

Grishchenko

et al. 2011

J Eng Phys Thermophy

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The influence of the dielectric barrier discharge plasma on the total aerodynamic drag of the Zhukovskii airfoil has been investigated. With the use of the Pitot-Prandtl tube the velocity distribution of discharge-induced ion wind at a distance of 18 mm from the trailing edge of the airfoil has been measured experimentally. It has been shown that the influence of the discharge leads to a decrease in the aerodynamic drag by a value from 10 to 34% depending on the incident flow parameters and the operating conditions of the discharge system.Introduction. The application of the dielectric barrier discharge for controlling the gas flow and its influence on the aerodynamic drag of flying vehicles is now a topical and promising trend in scientific investigations. Important parameters thereby are the velocity of ion wind induced by a near-surface discharge, as well as the structure of the ionized gas flow formed by it [1][2][3][4][5][6][7].The velocity distribution in the near and far wakes behind a streamlined body in the presence of a surface discharge was investigated in a subsonic aerodynamic channel at velocities of 4.6 and 6.8 m ⁄ s [2, 4]. The presented velocity distributions point to a pressing of the boundary layer to the surface near which the dielectric barrier discharge forms a plasma layer, which agrees with the results obtained in [8]. The use of the dielectric barrier discharge plasma permits also solving the problem of gas flow separation from the surface of the wing [9]. The authors of [10] managed to prevent gas flow separation at an angle of attack of 5 o for velocities of up to 2.85 m ⁄ s, and with increasing angle of attack to 15-21 o for velocities of up to 75 m ⁄ s.Because the ion wind velocity strongly depends on the configuration of the system of discharge electrodes, it is difficult to determine what conditions are the most effective in terms of obtaining the maximum velocity of the discharge-induced flow. In the two-electrode system at a distance of 18 mm from the edge of the high-voltage electrode a velocity of ion wind equal to 3 m ⁄ s was registered [6], and the maximum value of the velocity near the needle electrode equal to 6 m ⁄ s was obtained in [1].Setting an additional electrode permits decreasing the space charge accumulation and, as a result, weakening the electric field shielding by charged particles near the discharge electrodes. For these purposes, additional coronaforming or grounded electrodes set in the immediate vicinity of the dielectric surface are used [11]. In the three-electrode system of dielectric barrier discharge formation, a velocity of 4.5 m ⁄ s at a distance of 30-48 mm from the edge of the high-voltage electrode was attained [12].The maximum value of the ion wind velocity at a distance of 18 mm from the trailing edge obtained in the present paper is 1.6 m ⁄ s, which is several times higher than the value equal to 0.35 m ⁄ s given in [12].The results of experimental measurements of the reactive force induced by the ion wind presented by different authors do not ex...

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supporting

confidence: 88%

Influence of the barrier discharge on the aerodynamic drag of the Zhukovskii airfoil under various air flow conditions

Khramtsov

Penyazkov

Grishchenko

et al. 2011

J Eng Phys Thermophy

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“…In addition, it has been clarified that the use of unsteady actuation gives a better of capability to the separation control compared with steady actuation [29,31,32]. The unsteady actuation is called the "burst mode" in this study, and the steady actuation is called the "normal mode."…”

mentioning

confidence: 96%

“…Furthermore, the voltage, frequency, and waveform of the AC input are also important factors for the performance of the plasma actuator; thus, the effects of these parameters have been investigated [28][29][30]. In addition, it has been clarified that the use of unsteady actuation gives a better of capability to the separation control compared with steady actuation [29,31,32].…”

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confidence: 98%

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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“…Post et al apply DBD plasma actuator to the airfoil 10 and they show that use of unsteady input voltage that is called "duty cycle" or "burst wave" gives higher separation control capability with less input energy. [11][12][13] The burst wave is the unsteady alternative current switched on and off periodically as shown in Fig. 2.…”

Section: Introductionmentioning

confidence: 98%

Burst Frequency Effect of DBD Plasma Actuator on the Control of Separated Flow over an Airfoil

Asada

Fujii

2012

6th AIAA Flow Control Conference

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The flow fields around NACA0015 airfoil, separation over which is controlled by a DBD plasma actuator are simulated by implicit large eddy simulation with compact difference scheme, and the burst frequency effect of DBD plasma actuator on the control of separated flow over the airfoil is discussed. The Reynolds number based on chord length is set to 63,000 and the angle of attack is set to 14 [deg]. The DBD plasma actuator is installed at the 0 % and 5 % chord length from the leading edge, and actuated in burst mode. For the burst mode, the nondimensional burst frequency is set to 1 and 6. Through the present analysis, the two mechanisms of separation control are discussed. The first mechanism enhance the vortex shedding from the separation shear layer and avoid the massive separation from the leading edge on burst mode with nondimensional burst frequency of 1. The second mechanism improves the airfoil performance by suppressing the separation region on the burst mode with nondimensional burst frequency of 6. In addition, it is clarified that the first mechanism is more sensitive to the location of the DBD plasma actuator than the second mechanism and it is associated with large fluctuation of lift.

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Pulsed Discharge Actuators for Rectangular Wing Separation Control

Cited by 65 publications

References 4 publications

Influence of the barrier discharge on the aerodynamic drag of the Zhukovskii airfoil under various air flow conditions

Influence of the barrier discharge on the aerodynamic drag of the Zhukovskii airfoil under various air flow conditions

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

Burst Frequency Effect of DBD Plasma Actuator on the Control of Separated Flow over an Airfoil

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