Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators

Post, Martiqua; Corke, Thomas

doi:10.2514/1.2929

Cited by 528 publications

(173 citation statements)

References 6 publications

Supporting

Mentioning

166

Contrasting

Unclassified

Order By: Relevance

“…6 Furthermore, the actuator can be operated at atmospheric pressures and does not require a sophisticated power supply. SDBDs have the ability to manipulate the boundary layer, 7-11 film cooling 12 and delaying separation on turbine blades 13 and aerofoils, 14 and manipulate the transition point, 15 control separation on stationary 16 and oscillating aerofoils 17 leading to reduced noise levels. 18 However, to date, they have only been used at micro air vehicle Reynolds numbers (e.g., on small unmanned aircraft 19,20 ).…”

Section: Introductionmentioning

confidence: 99%

Plasma actuator: Influence of dielectric surface temperature

Erfani

Zare‐Behtash

Kontis

2012

Experimental Thermal and Fluid Science

View full text Add to dashboard Cite

Plasma actuators have become the topic of interest of many researchers for the purpose of flow control. They have the advantage of manipulating the flow without the need for any moving parts, a small surface profile which does not disturb the free stream flow, and the ability to switch them on or off depending on the particular situation (active flow control). Due to these characteristics they are becoming very popular for flow control over aircraft wings. The objective of the current study is to examine the effect of the actuator surface temperature on its performance. This is an important topic to understand when dealing with real life aircraft equipped with plasma actuators. The temperature variations encountered during a flight envelope may have adverse effects in actuator performance. A peltier heater along with dry ice are used to alter the actuator temperature, while particle image velocimetry (PIV) is utilised to analyse the flow field. The results show a significant change in the induced flow field by the actuator as the surface temperature is varied. It is found that for a constant peak-to-peak voltage the maximum velocity produced by the actuator depends directly on the dielectric surface temperature. The findings suggest that by changing the actuator temperature the performance can be maintained or even altered at different environmental conditions.

show abstract

Section: Introductionmentioning

confidence: 99%

Plasma actuator: Influence of dielectric surface temperature

Erfani

Zare‐Behtash

Kontis

2012

Experimental Thermal and Fluid Science

View full text Add to dashboard Cite

show abstract

“…[1][2][3][4][5] Their simple construction, robustness, and low power requirements render them ideal for active flow control in a variety of scenarios. Numerous studies have been performed in utilizing these actuators, among others, for airfoil separation control 6,7 and boundary layer control. [8][9][10] Several parametric and optimization studies have been performed for maximizing the produced body force and induced velocity.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on dielectric barrier discharge actuators operating in pulse mode

Kotsonis

Veldhuis

2010

Journal of Applied Physics

View full text Add to dashboard Cite

An experimental investigation is performed on the operation of dielectric barrier discharge plasma actuators used as manipulators of secondary and unsteady flow structures such as boundary layer instabilities or shedding vortices. The actuators are tested mainly in pulse mode. High sample rate hot-wire measurements of the induced velocity field downstream of the actuator are taken for the cases of pulse actuation in still air as well as in a laminar boundary layer. Complementary voltage and current measurements are taken to calculate power consumption. Additionally, a study on the influence of the pulse frequency and duty cycle of actuation is performed. Results show the effectiveness of plasma actuators in inducing fluctuating components of velocity when operated in pulse mode. Spectral analysis reveals the connection between the actuator driving signal and the induced flowfield. The magnitude as well as the consistency of the resulting fluctuating field are dependent on both the duty cycle and the pulse frequency. An empirical operational envelope based on phenomenological observations is proposed, for the use of the actuators at specific flow and operational conditions given in the paper.

show abstract

“…This illustrates that the boundary layer was forced to attach. Further details on this are given by Post & Corke [6,7]. It has been shown in the literature, for example, by Seifert et al [23] and Greenblatt & Wygnanski [24], that the introduction of periodic disturbances near the separation location can prevent or delay the onset of flow separation.…”

Section: Introductionmentioning

confidence: 99%

Sensing and control of flow separation using plasma actuators

Corke

Bowles

et al. 2011

Phil. Trans. R. Soc. A.

Self Cite

View full text Add to dashboard Cite

Single dielectric barrier discharge plasma actuators have been used to control flow separation in a large number of applications. An often used configuration involves spanwise-oriented asymmetric electrodes that are arranged to induce a tangential wall jet in the mean flow direction. For the best effect, the plasma actuator is placed just upstream of where the flow separation will occur. This approach is generally more effective when the plasma actuator is periodically pulsed at a frequency that scales with the streamwise length of the separation zone and the free-stream velocity. The optimum frequency produces two coherent spanwise vortices within the separation zone. It has been recently shown that this periodic pulsing of the plasma actuator could be sensed by a surface pressure sensor only when the boundary layer was about to separate, and therefore could provide a flow separation indicator that could be used for feedback control. The paper demonstrates this approach on an aerofoil that is slowly increasing its angle of attack, and on a sinusoidally pitching aerofoil undergoing dynamic stall. Short-time spectral analysis of time series from a static pressure sensor on the aerofoil is used to determine the separation state that ranges from attached, to imminent separation, to fully separated. A feedback control approach is then proposed, and demonstrated on the aerofoil with the slow angle of attack motion.

show abstract

Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators

Cited by 528 publications

References 6 publications

Plasma actuator: Influence of dielectric surface temperature

Plasma actuator: Influence of dielectric surface temperature

Experimental study on dielectric barrier discharge actuators operating in pulse mode

Sensing and control of flow separation using plasma actuators

Contact Info

Product

Resources

About