Sensing and control of flow separation using plasma actuators

Corke, Thomas; Bowles, Patrick; He, Chuan; Matlis, Eric

doi:10.1098/rsta.2010.0356

Cited by 48 publications

(28 citation statements)

References 25 publications

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“…These devices usually operate at frequencies between 50 Hz and 500 kHz and the required voltage is typically a few kilovolts. Commonly, they have been applied to flow separation applications with extensive studies being performed over airfoils, which is reviewed by Corke et al [33] in this Theme Issue.…”

Section: Experimental Set-upmentioning

confidence: 99%

Turbulent boundary-layer control with plasma actuators

Choi

Jukes

Whalley

2011

Phil. Trans. R. Soc. A.

148

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This paper reviews turbulent boundary-layer control strategies for skin-friction reduction of aerodynamic bodies. The focus is placed on the drag-reduction mechanisms by two flow control techniques-spanwise oscillation and spanwise travelling wave, which were demonstrated to give up to 45 per cent skin-friction reductions. We show that these techniques can be implemented by dielectric-barrier discharge plasma actuators, which are electric devices that do not require any moving parts or complicated ducting. The experimental results show different modifications to the near-wall structures depending on the control technique.

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Section: Experimental Set-upmentioning

confidence: 99%

Turbulent boundary-layer control with plasma actuators

Choi

Jukes

Whalley

2011

Phil. Trans. R. Soc. A.

148

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“…This directly adds momentum into the boundary layer which may re-energize the fluid, promote transition or initiate instabilities so that flow separation can be delayed, controlled or completely avoided. This is most effective when the actuators are located just upstream of the separation point (Huang, Corke & Thomas 2006a;Jukes & Choi 2009a;Corke et al 2011), and pulsed periodically (Corke, He & Patel 2004;Huang, Corke & Thomas 2006b;Greenblatt et al 2008;Jukes & Choi 2009b), which can be utilized in efficient flow control strategies (Jukes & Choi 2009c). …”

Section: Dbd Plasma Flow Controlmentioning

confidence: 99%

On the formation of streamwise vortices by plasma vortex generators

Jukes

Choi

2013

J. Fluid Mech.

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The streamwise vortices generated by dielectric-barrier-discharge plasma actuators in the laminar boundary layer were investigated using particle image velocimetry to understand the vortex-formation mechanisms. The plasma vortex generator was oriented along the primary flow direction to produce a body force in the spanwise direction. This created a spanwise-directed wall jet which interacted with the oncoming boundary layer to form a coherent streamwise vortex. It was found that the streamwise vortices were formed by the twisting and folding of the spanwise vorticity in the oncoming boundary layer into the outer shear layer of the spanwise wall jet, which added its own vorticity to increase the circulation along the actuator length. This is similar to the delta-shaped, vane-type vortex generator, except that the circulation was enhanced by the addition of the vorticity in the plasma jet. It was also observed that the plasma vortex was formed close to the wall with an enhanced wall-ward entrainment, which created strong downwash above the actuator.

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“…Position and actuation strategies of these devices are key points in their effectiveness in flow control over aerodynamic surfaces. Many studies have been accomplished over airfoils [65][66][67][68][69][70][71][72], diffusers [73,74], and wind [10, 11 and 75] and turbine [8,9] blades, in order to enhance fluid-dynamic performance. Moreover, the adoption of these devices over landing gears and trailing edge surfaces have demonstrated the possibility to obtain a noise reduction effect [76][77][78].…”

Section: Dbd Aerodynamic Actuators: Flow Manipulationmentioning

confidence: 99%

Active Flow Control by Using Plasma Actuators

Neretti¹

2016

Recent Progress in Some Aircraft Technologies

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Active flow control has recently received an increasing attention since it allows to directly manipulate the flow-field around a surface only when it is effectively requested. Aerodynamic plasma actuators supplied by a dielectric barrier discharge (DBD) can be used for this purpose. Usually, sinusoidal voltages in the range 5-50 kV peak and frequencies between 1 and 100 kHz are utilized to ignite this plasma typology. The surface discharge produced by these devices is able to tangentially accelerate the flow field by means of the electrohydrodynamic (EHD) interaction. DBDs generate non-thermal plasmas characterized by low input energies and limited temperature increments. Plasma actuators can be easily designed by following the shape of the aerodynamic body and can be used over heat-sensitive surfaces. These aerodynamic devices have demonstrated to produce boundary layer modifications with induced speeds up to 10 m/s. Their use over airfoils, flaps, and blades have shown the possibility to delay the transition between laminar to turbulent regime, to prevent flow separation enhancing lift and reducing drag. Moreover, the adoption of these actuators over landing gears and trailing edges may induce a noise reduction effect. Dielectric materials, electrodes configuration, and supplying waveforms are most relevant parameters to be considered to enhance actuator performance. On a parallel plane, on/off actuation strategy is a key point in the use of these devices when utilized over aerodynamic surfaces impinged within an external flow.

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Sensing and control of flow separation using plasma actuators

Cited by 48 publications

References 25 publications

Turbulent boundary-layer control with plasma actuators

Turbulent boundary-layer control with plasma actuators

On the formation of streamwise vortices by plasma vortex generators

Active Flow Control by Using Plasma Actuators

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