Flow structures in flat plate boundary layer induced by pulsed plasma actuator

Zhang, Panfeng; Liu, AiBing; Wang, Jinjun

doi:10.1007/s11431-010-4100-7

Cited by 26 publications

(14 citation statements)

References 38 publications

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“…Khoshkhoo et al [16] explored the effects of body force over a NACA0015 airfoil with this model and found that dimensions, magnitude and the location of the body force all have significant impact on the separation control. Zhang et al [17] employed it to study the flow structures of the boundary layer in a flat plate induced by a plasma actuator. Yu et al [11] used the linear body approach and found that the vortex pairs, which are reduced by a plasma, would enhance the energy exchanged between the near wall region and the free stream.…”

Section: Introductionmentioning

confidence: 99%

Effect of DBD plasma excitation characteristics on turbulent separation over a hump model

Ma¹,

Wang²,

Zhu³

2018

Plasma Sci. Technol.

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In this paper, the effect of dielectric-barrier discharge plasma excitation characteristics on turbulent boundary layer separation over a hump is investigated using computational fluid dynamics. Four different turbulence models were used for verification. The Reynolds stress model showed the best agreement with the experimental data, in general. Based on the verification and validation, the effect of duty cycle and excitation frequency on the turbulent flow separation were investigated. The results showed that the pulsed plasma excitation could effectively suppress the flow separation by mixing augmentation. With increasing duty cycle and excitation frequency, the flow separation first increased, then decreased again. The optimal duty cycle was 0.75 and the optimal excitation frequency was 50 Hz.

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Section: Introductionmentioning

confidence: 99%

Effect of DBD plasma excitation characteristics on turbulent separation over a hump model

Ma¹,

Wang²,

Zhu³

2018

Plasma Sci. Technol.

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“…Thanks to its simple construction, convenient installation and fast time response, the plasma actuator has attracted much attention in aeronautical applications. [1][2][3][4][5][6][7][8][9][10][11][12][13] Typical asymmetrical DBD plasma actuators include an exposed and covered electrode separated by a thin insulating material, with the covered electrode encapsulated by the dielectric material and the exposed electrode exposed to the air, as shown in Fig. 1.…”

Section: Introductionmentioning

confidence: 99%

Coherent structures induced by dielectric barrier discharge plasma actuator

Zhang

Choi

et al. 2017

Mod. Phys. Lett. B

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The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of f 0 = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.

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“…They are simple to implement and computationally cheap. Therefore, they are used in different applications [20,21].…”

Section: Introductionmentioning

confidence: 99%

Flow separation control over airfoils using DBD plasma body force

Khoshkhoo

Jahangirian

2014

J Braz. Soc. Mech. Sci. Eng.

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usually the flow behavior is laminar, which is important for control of the flow [2].Methods to flow separation control include active and passive techniques which are based on energy expenditure and controlled by command. Passive separation control techniques generally constitute geometric changes such as vortex generator, slotted flaps/slats, etc. These control elements are effective if the aircraft is operating in a flight regime that is in their design envelope. However, in off-design conditions, passive control elements can have detrimental effects that are often manifested in the form of increased drag [3]. Active separation control techniques have benefits of passive techniques without their disadvantage in off-design conditions. Also, these techniques have the potential to be implemented in a feedback system that can create more benefits in flight efficiency and maneuverability [3].Dielectric barrier discharge (DBD) plasma actuator is one of the active flow control devices that have been successfully used in aerodynamic flow control applications. Thus, considerable researches have been carried out on DBD plasma actuators over the past decade [4]. The examples of aerodynamic flow control applications by DBD plasma actuators include separation control in leading edge [5, 6], trailing edge [3, 7], bluff bodies [8], low pressure turbine blade [9, 10], axial compressor [11], flow control over a hump [12], Stabilizing a laminar boundary layer [13, 14], bluff body induced sound control [15], airfoil lift increasing [16], etc. Special characteristics of DBD plasma actuator over traditional flow control devices include reduction in size, weight and drag, increasing reliability, inexpensiveness, wide frequency bandwidth, rapid on-off capability, no moving parts, low energy consumption, and increasing stealth.The actuator consists of two asymmetrical metal electrodes separated by a dielectric layer, normally kapton, or Abstract The body force effects of plasma origin on the flow over a NACA 0015 airfoil are investigated by numerical simulation. The plasma actuator effect is estimated based on a phenomenological DBD plasma model coupled with 2-dimentional compressible Navier-Stokes equations. The equations are solved using an explicit finite volume method on unstructured grids. The responses of a separated flow field to the effects of a plasma actuator body force in various magnitudes and locations are presented. Also the effects of plasma region dimensions on the flow separation control are studied. It is found that the dimensions of plasma region, the magnitude of the body force, and the location of the plasma actuator all have significant impacts on the separation control.

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Flow structures in flat plate boundary layer induced by pulsed plasma actuator

Cited by 26 publications

References 38 publications

Effect of DBD plasma excitation characteristics on turbulent separation over a hump model

Effect of DBD plasma excitation characteristics on turbulent separation over a hump model

Coherent structures induced by dielectric barrier discharge plasma actuator

Flow separation control over airfoils using DBD plasma body force

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