Flat plate drag reduction using plasma-generated streamwise vortices

Cheng, Xiuwen; Wong, Chi-Yin; Hussain, Fazle; Schröder, Wolfgang; Zhou, Yu

doi:10.1017/jfm.2021.311

Cited by 43 publications

(14 citation statements)

References 82 publications

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“…The data of both uncontrolled and controlled boundary layers fit the law of the wall, i.e. u * =y * , for y * in the range 3.8-5, which is similar to the results of Cheng et al [11].…”

Section: Single-point Measurement Of Local Drag Reductionsupporting

confidence: 87%

“…The dielectric barrier discharge (DBD) plasma flow control method [3][4][5][6], as an active flow control technology, has recently attracted a great deal of interest because of its advantages, e.g. no moving mechanical parts, a simple structure and a rapid response [7][8][9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

“…This was consistent with the premise that the control would actively intervene with an autonomous cycle involving lift-up and break-up of coherent streamwise vorticity that is associated with the low-speed wall streak structure. Cheng et al [11] found a DR of up to 26% downstream of the actuators using plasma-generated large-scale streamwise vortices, and these vortices pushed numerous meandering streaks to form a stabilized streak, leading to suppression of transient growth and near-wall turbulent production. Mahfoze and Laizet [12] simulated near-wall spanwise-oriented jets to control the turbulent boundary layer, in which the jets liked the flow generated by unidirectional pulsed-DC DBD actuators [2], and obtained a DR of 33%.…”

Section: Introductionmentioning

confidence: 99%

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Turbulent boundary layer control with DBD plasma actuators

Li¹,

Wu²,

Gao³

et al. 2023

Plasma Sci. Technol.

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The flat plate turbulent boundary layer at Reτ = 1140 is manipulated using a spanwise array of bidirectional dielectric barrier discharge (DBD) plasma actuators. Based on the feature of no moving mechanical parts of DBD plasma control technology and hot wire anemometer velocity measurements, a novel convenient method of local drag reduction (DR) measurement is proposed by measuring single point velocity within the linear region of the viscous sublayer. Analyzing the premise of using the method, the maximum effective measurement range of −73.1% < DR < 42.2% is obtained according to the experimental environment in this work. The local drag decreases downstream of the center of two adjacent upper electrodes and increases downstream of the upper electrodes. The magnitude of the local DR increases with increasing voltage and decreases as it moves away from the actuators. For the spanwise position in between, the streamwise distribution of the local DR is very dependent on the voltage. The VITA detection results reveal that all bursting intensities are reduced compared to the baseline, and the amount of reduction is comparable to the absolute values of the local DR. Compared with previous results, we infer that the control mechanism is that many meandering streaks are combined together into single stabilized streaks.

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“…The data of both uncontrolled and controlled boundary layers fit the law of the wall, i.e. u * =y * , for y * in the range 3.8-5, which is similar to the results of Cheng et al [11].…”

Section: Single-point Measurement Of Local Drag Reductionsupporting

confidence: 87%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Turbulent boundary layer control with DBD plasma actuators

Li¹,

Wu²,

Gao³

et al. 2023

Plasma Sci. Technol.

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“…During the plasma discharge the charged particles are subjected to the electric field generated by the asymmetric electrodes and collide with the neutral particles for momentum transfer, forming a directional jet from the exposed electrode to the buried electrode along the actuator surface. [4] DBD has many applications in active flow control, mainly lift increase and drag reduction, [5][6][7][8][9] noise reduction, [10,11] lateral force control [12,13] and suppression of flow separation. [14][15][16][17][18] The cited studies have demonstrated the flow control performance of DBD actuators.…”

Section: Introductionmentioning

confidence: 99%

Flow control performance evaluation of a tri-electrode sliding discharge plasma actuator

Zheng

LIU

et al. 2023

Chinese Phys. B

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Tri-electrode sliding discharge (TED) plasma actuators are formed by adding a direct current (DC) exposed electrode to conventional dielectric barrier discharge (DBD) plasma actuators. TED has three discharge modes depending on the polarity and amplitude of the DC supply: DBD discharge, extended discharge, and sliding discharge. This paper evaluates the plasma actuator's electrical, aerodynamic, and mechanical characteristics based on energy analysis, particle image velocimetry (PIV) experiments, and N-S equations calculation. The flow control performances of different discharge modes are quantitatively analyzed based on characteristic parameters. The results show that flow control performances in both extended discharge and sliding discharge are more significant than that of DBD, mainly because of the significantly higher body force of TED compared to DBD, which is up to 141%. However, conductivity loss is the primary power loss caused by the DC polar for TED discharge. Therefore, power consumption can be reduced by optimizing the dielectric material and thickness, thus improving the flow control performance of plasma actuators.

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“…The flow field characteristics of a drag plate located behind the cockpit on the back of the fuselage are simulated, and the effects of the width and deflection angle of the air brake on the pitching moment are studied (Cui et al ., 2018; Jafari et al ., 2018). The upper deflection of the spoiler and the upper deflection of the hinge flaps can produce greater rolling torque and avoid unnecessary increase of resistance (Wang et al ., 2017; Cheng et al ., 2021). An automatic triangle mesh generation method based on bubbles is presented (Wang et al ., 2019a, b).…”

Section: Introductionmentioning

confidence: 99%

Quantitative calculation of electromagnetic scattering characteristics from drag plate of aircraft afterbody

Zhou,

Huang

2023

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PurposeThis paper aims to discuss the electromagnetic scattering characteristics of the afterbody model with two drag plates.Design/methodology/approachThe plane shape of the drag plate model is designed as a rectangle. High-precision unstructured grid technology is used to treat the target surface. A calculation method based on multiple tracking and dynamic scattering module is presented to calculate the radar cross section (RCS).FindingsThe results show that under the given observation conditions, the RCS and surface scattering characteristics of a single drag plate change with the increase of the opening angle, which makes the forward RCS of the afterbody model change more than 8.43 dBm2. The opening of two resistance plates at different fixed angles has little effect on the peak value and position of the RCS of the afterbody model. The dynamic deflection of the two drag plates can bring 16.78 dBm2 fluctuations to the forward RCS of the afterbody model, and more than 25.59 dBm2 fluctuations to the side RCS.Practical implicationsThe installation positions of the drag plate on the aircraft are various, so the method in this paper can provide reference and support for RCS analysis of the speed brake at other positions.Originality/valueThe presented calculation method is of engineering value to analyze the electromagnetic scattering characteristics of the drag plate.

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Flat plate drag reduction using plasma-generated streamwise vortices

Abstract: Abstract

Cited by 43 publications

References 82 publications

Turbulent boundary layer control with DBD plasma actuators

Turbulent boundary layer control with DBD plasma actuators

Flow control performance evaluation of a tri-electrode sliding discharge plasma actuator

Quantitative calculation of electromagnetic scattering characteristics from drag plate of aircraft afterbody

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