Control of Airfoil Aerodynamic Performance Using Distributed Trapped Vorticity

DeSalvo, Michael; Glezer, Ari

doi:10.2514/6.2007-708

Cited by 14 publications

(9 citation statements)

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“…DeSalvo & Glezer [63,64,69] leveraged a hybrid actuation approach to control low-angle-of-attack aerodynamic characteristics of a swept aerofoil. The model had a fixed cross section based on a commercial aircraft configuration, a sweep angle of 27.1…”

Section: (B) Aerodynamic Control Of Aerofoils At Low Angles Of Attackmentioning

confidence: 99%

“…Bi-directional variation in the pitching moment can be effected using controlled trapped vorticity concentrations on the suction and pressure surfaces to alter the Kutta condition near the aerofoil's trailing edge [64]. The variation of C M with angle of attack when the hybrid actuators (similar to Gurney flaps) are mounted near x/c = 0.95 is shown in figure 4c for the baseline aerofoil and in the presence of the inactive and active actuators.…”

Section: (B) Aerodynamic Control Of Aerofoils At Low Angles Of Attackmentioning

confidence: 99%

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Some aspects of aerodynamic flow control using synthetic-jet actuation

Glezer

2011

Phil. Trans. R. Soc. A.

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Aerodynamic flow control effected by interactions of surface-mounted synthetic (zero net mass flux) jet actuators with a local cross flow is reviewed. These jets are formed by the advection and interactions of trains of discrete vortical structures that are formed entirely from the fluid of the embedding flow system, and thus transfer momentum to the cross flow without net mass injection across the flow boundary. Traditional approaches to active flow control have focused, to a large extent, on control of separation on stalled aerofoils by means of quasi-steady actuation within two distinct regimes that are characterized by the actuation time scales. When the characteristic actuation period is commensurate with the time scale of the inherent instabilities of the base flow, the jets can effect significant quasi-steady global modifications on spatial scales that are one to two orders of magnitude larger than the scale of the jets. However, when the actuation frequency is sufficiently high to be decoupled from global instabilities of the base flow, changes in the aerodynamic forces are attained by leveraging the generation and regulation of 'trapped' vorticity concentrations near the surface to alter its aerodynamic shape. Some examples of the utility of this approach for aerodynamic flow control of separated flows on bluff bodies and fully attached flows on lifting surfaces are also discussed.

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Section: (B) Aerodynamic Control Of Aerofoils At Low Angles Of Attackmentioning

confidence: 99%

Section: (B) Aerodynamic Control Of Aerofoils At Low Angles Of Attackmentioning

confidence: 99%

Some aspects of aerodynamic flow control using synthetic-jet actuation

Glezer

2011

Phil. Trans. R. Soc. A.

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“…The smallest model cavity of Lopez Mejia et al [7] is selected to accelerate computation here because the exact cavity of the actuator is not required to represent the effects of the synthetic jet on the aerodynamic properties [6,7]. The curved shape of the actuator is designed for the Coanda-like deflection of the separating flows toward the adjacent surface [1].…”

Section: A Computatoinal-fluid-dynamics Modelsmentioning

confidence: 99%

“…DeSalvo and Glezer [1] reported that a similar configuration of the actuators generates bidirectional change in aerodynamic forces. The actuation controls the wake vorticity trapped downstream of the actuators, which manipulates the Kutta condition of the airfoil [1]. The current synthetic jet actuators have a very high frequency that is even higher than the fundamental frequency of the external flow, namely the shedding frequency.…”

Section: Introductionmentioning

confidence: 99%

“…This jet flow is "synthesized" by periodically alternating ejection and suction of fluid through an orifice, which is produced by an oscillating pressure in an actuator cavity. Commonly, a piezoelectric diaphragm [1,2] or a piston [3] has been used to generate the oscillating pressure. This jet has zero-net mass flux but nonzero jet momentum, which makes it an effective fluid actuator in numerous flow-control applications, specifically aerodynamic applications.…”

Section: Introductionmentioning

confidence: 99%

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Simulation of Rapidly Maneuvering Airfoils with Synthetic Jet Actuators

et al. 2013

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Synthetic jet actuators are investigated for rapidly maneuvering airfoils that are regulated by a closed-loop control system. To support active flow-control simulations performed here, the closed-loop system and vehicle dynamics are coupled with computational fluid dynamics. High-frequency sinusoidal pitching simulations with and without synthetic jet actuation indicate that the current synthetic jet actuators provide bidirectional change in aerodynamic forces during rapid maneuvers whose time scales are of the same order as the flow time scales. Responses of a windtunnel airfoil are well represented in the current simulations, which allows us to predict the response of the system for dynamic conditions representative of free flight. The control system is able to execute rapid free-flight maneuvers. It is observed that the controller is responding to small fluctuations caused by vortex shedding from the trailing-edge actuators.

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Effect of trailing edge dual synthesis jets actuator on aerodynamic characteristics of a straight-bladed vertical axis wind turbine

Wang

Liu

et al. 2022

Energy

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Control of Airfoil Aerodynamic Performance Using Distributed Trapped Vorticity

Cited by 14 publications

References 1 publication

Some aspects of aerodynamic flow control using synthetic-jet actuation

Some aspects of aerodynamic flow control using synthetic-jet actuation

Simulation of Rapidly Maneuvering Airfoils with Synthetic Jet Actuators

Effect of trailing edge dual synthesis jets actuator on aerodynamic characteristics of a straight-bladed vertical axis wind turbine

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