Flight Control Using Wing-Tip Plasma Actuation

Boesch, Gilles; Vo, Huu Duc; Savard, Bruno; Wanko-Tchatchouang, Christelle; Mureithi, Njuki W.

doi:10.2514/1.44003

Cited by 29 publications

(14 citation statements)

References 14 publications

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“…This observation is in keeping with the previously proposed mechanism of control. Boesch et al 23 hypothesised from simulations with a symmetric wing at zero angle of attack, that the pressure side and tip centred electrodes opposed the rolling up of the shear layer. While the electrodes placed on the suction side were described as effectively blocking the flow around the tip at the origin of the tip vortex formation.…”

Section: A Streamwise Vorticity Contoursmentioning

confidence: 99%

“…The dielectric barrier discharge (DBD) plasma actuator is currently the most commonly used discharge for airflow control with ionic wind speeds of approximately 7 ms −1 . 21, 22 Boesch et al 23 investigated the concept of using a plasma actuator to modify the lift of a conventional wing for roll control at low angles of attack. The actuator was placed around a NACA 4418 rounded wing tip orientated such that momentum was added in the opposite direction to that of the cross-stream flow.…”

mentioning

confidence: 99%

“…However, a limiting factor for DBD actuators is the relatively low induced velocity. This limitation may explain why a relatively low freestream velocities was used in all of the tests (a maximum of 4 ms −1 tested by Agibalova et al 25 and a maximum of 15 ms −1 tested by Boesch et al 23 ).…”

mentioning

confidence: 99%

“…The configuration was similar to that used by Boesch et al 23 Particle image velocimetry measurements were acquired to understand the near field effect of the actuator on the tip vortex evolution. The dependency of the actuators performance on both angle of attack and freestream velocity has been examined.…”

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confidence: 99%

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Active Control of a Wing Tip Vortex with a Dielectric Barrier Discharge Plasma Actuator

Chappell

Angland

2012

6th AIAA Flow Control Conference

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An experimental investigation has been conducted into the active control of a wing tip vortex with a dielectric barrier discharge plasma actuator. The actuator was placed around the wing tip with the momentum added in the opposite direction to that of the cross stream flow. Particle image velocimetry measurements were performed on a low aspect ratio rounded tip NACA 0015 wing in a low speed wind tunnel at a maximum Reynolds number of 2.8 ×10 5 , based on the wing chord. Experiments were performed at various angles of attack. The current strength of the plasma actuator limited the maximum freestream velocity to 15 ms −1 . For low angles of attack (2 • and 6 • ), the near field results showed an increase in vortex size and a reduction in the core circulation when control was applied. The effectiveness of the actuator reduced with freestream velocity and angle of attack. The use of the plasma actuator was found to increase the velocity fluctuations close to the surface of the wing. At an angle of attack of 14 • , the actuator resulted in a smaller vortex and an increase in the core circulation. It was hypothesised that at this high angle of attack, the vorticity generated at the suction side electrodes was fed into the core, increasing the strength of the tip vortex. The results show that the potential of the plasma actuator for the near field control of the tip vortex is promising provided the angle of attack is low. NomenclatureA * Non-dimensionalised bounded within area of integration AR Aspect ratio b w Wing span, m C L Wing lift coefficient c Wing chord, m Re c Reynolds number based on main element chord r Radial distance measured from vortex centre, mm r 1 Radius of vortex, mm r max Maximum radial distance measured from vortex centre, mm S Surface area, m 2 s Wing semi-span, m t w Wing thickness, m U ∞ Freestream velocity, ms −1 v rms Root mean square velocity component in y direction, ms −1 v * θ Non-dimensionalised tangential velocity x, y, z Coorindates measured from model leading edge tip, m y c , z c Vortex centroid, m * PhD Student, Faculty of Engineering and the Environment. Student Member AIAA † Research Fellow, Faculty of Engineering and the Environment, Member AIAA.

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Section: A Streamwise Vorticity Contoursmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Active Control of a Wing Tip Vortex with a Dielectric Barrier Discharge Plasma Actuator

Chappell

Angland

2012

6th AIAA Flow Control Conference

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“…It was demonstrated that DBD actuators can be successfully applied to modify the vortex breakdown location but also to stabilize vortex when operating in burst mode. Plasma actuation on the wing tip vortex of rectangular wing [9][10][11] has been investigated experimentally and numerically and has shown different influences of the actuation on the wing tip vortex formation according to a suction or blowing effect produced by actuators. Results on aerodynamic performance modification, lift increase 8 for example, differ with the study cases.…”

Section: Introductionmentioning

confidence: 99%

Experimental studies of DBD actuator effects on wing tip vortex topology

Leroy

Molton²,

Carpels³

et al. 2012

6th AIAA Flow Control Conference

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Experiments studying the wing tip vortex, generated by a rectangular wing with a symmetric airfoil section and a straight tip, manipulated by surface plasma actuators are presented in this paper. Objectives are focused on modifying vortex development to alter streamwise vorticity downstream of the wing trailing edge. Actual limitation of the ionic wind magnitude obtained with DBD actuators leads to investigate vortex control by action on the transverse component of the freestream flow velocity. Different DBD arrangements installed near the wing tip were tested to examine effects of momentum addition, firstly on the pressure and suction side surfaces, and secondly, simultaneously located more precisely on the main vortex separation and attachment lines. Stereoscopic PIV measurements were performed in different planes orthogonal to the vortex development axis to visualize and characterize wing tip vortices. According to DBD arrangements, results of the actuation show a slight displacement of the wing tip vortex and a reduction of the mean streamwise vorticity level in its core. Nomenclature c = chord U 0 = freestream velocity X = chord axis Y = transverse axis Z = vertical axis U = chord axis velocity V = transverse axis velocity W = vertical axis velocity k = turbulent kinetic energy  x = streamwise vorticity

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Flow Structure Modification Using Plasma Actuation for Enhanced UAV Flight Control

Torres

2017

Advanced UAV Aerodynamics, Flight Stability and Control

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Flight Control Using Wing-Tip Plasma Actuation

Cited by 29 publications

References 14 publications

Active Control of a Wing Tip Vortex with a Dielectric Barrier Discharge Plasma Actuator

Active Control of a Wing Tip Vortex with a Dielectric Barrier Discharge Plasma Actuator

Experimental studies of DBD actuator effects on wing tip vortex topology

Flow Structure Modification Using Plasma Actuation for Enhanced UAV Flight Control

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