Lift and drag performances of an axisymmetric airfoil controlled by plasma actuator

Bénard, Nicolas; Jolibois, J.; Moreau, E.

doi:10.1016/j.elstat.2009.01.008

Cited by 128 publications

(75 citation statements)

References 12 publications

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“…Due to the limited applicability of the device, the effectiveness of control was restricted to relatively low Reynolds number of 100 000, such as those associated with MAVs. Applying a DBD plasma actuator at the leading edge of a NACA 0015 airfoil at the Reynolds number of 260 000, Benard, Jolibois & Moreau (2009) found that the stall angle was increased and the drag reduced. They found that an unsteady plasma actuation could result in a further increase in lift and a reduction in drag as compared to those by a steady actuation.…”

Section: Plasma Flow Controlmentioning

confidence: 99%

Flow control over an airfoil using virtual Gurney flaps

2015

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Flow control over a NACA 0012 airfoil is carried out using a dielectric barrier discharge (DBD) plasma actuator at the Reynolds number of 20 000. Here, the plasma actuator is placed over the pressure (lower) side of the airfoil near the trailing edge, which produces a wall jet against the free stream. This reverse flow creates a quasi-steady recirculation region, reducing the velocity over the pressure side of the airfoil. On the other hand, the air over the suction (upper) side of the airfoil is drawn by the recirculation, increasing its velocity. Measured phase-averaged vorticity and velocity fields also indicate that the recirculation region created by the plasma actuator over the pressure surface modifies the near-wake dynamics. These flow modifications around the airfoil lead to an increase in the lift coefficient, which is similar to the effect of a mechanical Gurney flap. This configuration of DBD plasma actuators, which is investigated for the first time in this study, is therefore called a virtual Gurney flap. The purpose of this investigation is to understand the mechanism of lift enhancement by virtual Gurney flaps by carefully studying the global flow behaviour over the airfoil. First, the recirculation region draws the air from the suction surface around the trailing edge. The upper shear layer then interacts with the opposite-signed shear layer from the pressure surface, creating a stronger vortex shedding from the airfoil. Secondly, the recirculation region created by a DBD plasma actuator over the pressure surface displaces the positive shear layer away from the airfoil, thereby shifting the near-wake region downwards. The virtual Gurney flap also changes the dynamics of laminar separation bubbles and associated vortical structures by accelerating laminar-to-turbulent transition through the Kelvin-Helmholtz instability mechanism. In particular, the separation point and the start of transition are advanced. The reattachment point also moves upstream with plasma control, although it is slightly delayed at a large angle of attack.

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Section: Plasma Flow Controlmentioning

confidence: 99%

Flow control over an airfoil using virtual Gurney flaps

2015

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“…Generally, a lot of investigators studied lift and drag performances of NACA airfoil. Bhat enhancement of the air foil performance by using a plasma actuator in steady and unsteady models [2]. Yao et al, have computed aerodynamic performance analysis of NACA0018 wind turbine airfoil by using numerical simulation method.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigations of Lift and Drag Performances of NACA 0015 Wind Turbine Airfoil

Şahi̇n¹,

Acır²

2015

IJMMM

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Abstract-In the present work, we studied numerical and experimentally analysis lift and drag performances of NACA 0015 airfoil at different attack angle at low Reynolds numbers (Re) by measuring the forces every two degrees from 0° to 20°. The experiment test was conducted in low speed wind tunnel, and the numerical analysis was performed using CFD program which was FLUENT. The results obtained from experiment and numerical were compared. In this study, stall angle depended on turbulent occurred behind airfoil was determined. As result, effect of the stall angle of airfoil performance was investigated.Index Terms-Angle of attack, CFD, NACA 0015, wind tunnel.

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“…The induced velocity fluctuation frequencies could be changed by modulation of signals. Bernard et al [8] examined the effect of plasma actuator to NACA0015 airfoil aerodynamic performance with steady and unsteady actuations. They demonstrated that the plasma actuator improves the lift coefficient, reduces the drag coefficient and delays the stall angle.…”

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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Lift and drag performances of an axisymmetric airfoil controlled by plasma actuator

Cited by 128 publications

References 12 publications

Flow control over an airfoil using virtual Gurney flaps

Flow control over an airfoil using virtual Gurney flaps

Numerical and Experimental Investigations of Lift and Drag Performances of NACA 0015 Wind Turbine Airfoil

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

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