Pulsed Plasma Actuators for Active Flow Control at MAV Reynolds Numbers

Göksel, B.; Greenblatt, David; Rechenberg, Ingo; Kastantin, Y.; Nayeri, Christian Navid; Paschereit, Christian Oliver

doi:10.1007/978-3-540-71439-2_3

Cited by 13 publications

(11 citation statements)

References 8 publications

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“…Similar effects were observed previously, for example, using piezoelectric zero-mass-fl ux jet actuators (Margalit et al, 2002). This observation was exploited by Göksel et al (2006Göksel et al ( , 2007 to perform a series of experiments in the range 3000 £ Re £ 80,000, discussed later in this chapter. At lower Reynolds numbers, the proportion of actuator momentum, and therefore control authority, increases.…”

Section: Electro-and Magnetohydrodynamic Actuationsupporting

confidence: 68%

Fundamentals and Applications of Modern Flow Control

Joslin¹,

Miller²,

Miller³

2009

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Section: Electro-and Magnetohydrodynamic Actuationsupporting

confidence: 68%

Fundamentals and Applications of Modern Flow Control

Joslin¹,

Miller²,

Miller³

2009

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“…Goksel et al [10] examined the control of air flow separation and aerodynamic performances using plasma actuator at Reynolds numbers 20,500≤Re≤50,000 on Eppler E338 airfoil by steady and unsteady actuations. They demonstrated that lift coefficient is increased by decreasing duty cycle, and hence the input power, for duty cycles 3%.…”

Section: Introductionmentioning

confidence: 99%

Active Control of Flow around NACA 0015 Airfoil by Using DBD Plasma Actuator

Akansu

Karakaya

Şanlisoy

2013

EPJ Web of Conferences

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Abstract. In this study, effect of plasma actuator on a flat plate and manipulation of flow separation on NACA0015 airfoil with plasma actuator at low Reynolds numbers were experimentally investigated. In the first section of the study, plasma actuator which consists of positive and grounded electrode couple and dielectric layer, located on a flat plate was actuated at different frequencies and peak to peak voltages in range of 3-5 kHz and 6-12 kV respectively. The induced air flow velocity on the surface of flat plate was measured by pitot tube at different locations behind the actuator. The influence of dielectric thickness and unsteady actuation with duty cycle was also examined. In the second section, the effect of plasma actuator on NACA0015 airfoil was studied at Reynolds number 15000 and 30000. Four plasma actuators were placed at x/C = 0.1, 0.3, 0.5 and 0.9, and different electrode combinations were activated by sinusoidal signal. Flow visualizations were done when the attack angles were 0°, 5°, 10°, 15° and 20°. The results indicate that up to the 15° attack angle, the separated flow was reattached by plasma actuator at 12kV peak to peak voltage and 4 kHz frequency. However, 12 kV pp voltage was insufficient to reattach the flow at 20° angle of attack. The separated flow could be reattached by increasing the voltage up to 13 kV. Lift coefficient was also increased by the manipulated flow over the airfoil. Results showed that even high attack angles, the actuators can control the flow separation and prevent the airfoil from stall at low Reynolds numbers.

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“…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 ). Their benefits have not been fully utilised on large scales since the effectiveness of plasma actuators is limited by the maximum induced velocity they can achieve.…”

Section: Introductionmentioning

confidence: 99%

Plasma actuator: Influence of dielectric surface temperature

Erfani

Zare‐Behtash

Kontis

2012

Experimental Thermal and Fluid Science

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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.

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Pulsed Plasma Actuators for Active Flow Control at MAV Reynolds Numbers

Cited by 13 publications

References 8 publications

Fundamentals and Applications of Modern Flow Control

Fundamentals and Applications of Modern Flow Control

Active Control of Flow around NACA 0015 Airfoil by Using DBD Plasma Actuator

Plasma actuator: Influence of dielectric surface temperature

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