Modification of lifting body aerodynamics using synthetic jet actuators

Smith, Douglas R.; Amitay, Michael; Kibens, Valdis; Parekh, David; Glezer, Ari

doi:10.2514/6.1998-209

Cited by 164 publications

(69 citation statements)

References 15 publications

(21 reference statements)

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“…This alteration modifies the location of the separation point on the surface of the body. By altering the separation point as well as the characteristics of the downstream wake, synthetic jet actuation allows for the lift and drag forces experienced by the object to be altered [10,[15][16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Numerical Characterisation of Active Drag and Lift Control for a Circular Cylinder in Cross-Flow

McDonald

Persoons

2017

Applied Sciences

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Synthetic jet actuators have shown promise to control drag and lift for a bluff body in cross-flow. Using unsteady RANS CFD modelling, a significant modification of the drag coefficient for a circular cylinder in cross-flow at = 3900 is achieved by varying the actuation frequency. The variation in actuation frequency corresponds to a range in Stokes number of 2.4 < < 6.4. The trends in drag coefficient modification largely agree with the findings of past publications, achieving a maximum drag reduction at = 4.9 for a fixed jet Reynolds number of the synthetic jet of = 12. A decrease in the adverse pressure gradient near the jet orifice correlated with a momentum increase in the viscous sublayer and stronger vortical structures at the rear of the cylinder. In these same conditions, a decrease in turbulence intensity was observed in the far field wake, which is a relevant finding in the context of wind and tidal turbine arrays.

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Section: Introductionmentioning

confidence: 99%

Numerical Characterisation of Active Drag and Lift Control for a Circular Cylinder in Cross-Flow

McDonald

Persoons

2017

Applied Sciences

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“…Though C P was measured by the interval of α = 1º, a couple of meaningful flow characteristics are displayed. A constant pressure region starts to appear near the leading edge at α = 12º, implying that a separation bubble begins to grow over the stall angle [37,38]. A higher angle of attack makes the separation bubble larger, leading to a flat C P distribution along the airfoil upper surface.…”

Section: Verification Of Separation Control Capability 431 Synthetimentioning

confidence: 99%

Experimental and Computational Study on Separation Control Performance of Synthetic Jets with Circular Exit

Kim¹,

Lee²,

Jun-Hee³

et al. 2016

International Journal of Aeronautical and Space Sciences

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This paper presents experimental and computational investigations of synthetic jets with a circular exit for improving flow control performance. First, the flow feature and vortex structure of a multiple serial circular exit were numerically analyzed from the view point of flow control effect under a cross flow condition. In order to improve separation control performance, experimental and numerical studies were conducted according to several key parameters, such as hole diameter, hole gap, the number of hole, jet array, and phase difference. Experiments were carried out in a quiescent condition and a forced separated flow condition using piezoelectrically driven synthetic jets. Jet characteristics were compared by measuring velocity profiles and pressure distributions. The interaction of synthetic jets with a freestream was examined by analyzing vortical structure characteristics. For separation control performance, separated flow over an airfoil at high angles of attack was employed and the flow control performance of the proposed synthetic jet was verified by measuring aerodynamic coefficient. The circular exit with a suitable hole parameter provides stable and persistent jet vortices that do beneficially affect separation control. This demonstrates the flow control performance of circular exit array could be remarkably improved by applying a set of suitable hole parameters.

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“…Traditional separation control strategy uses actuation coupling to the narrow-band receptivity of the separating flow at the unstable Strouhal numbers of the near wake (e.g., St D ~ O(1), Hsiao et al 1990, Neuberger and Wygnanski 1987, Williams et al 1991, Chang et al 1992, Seifert et al 1993). An alternative approach uses actuation at substantially higher frequencies to decouple the global flow instabilities from fluidic modification of the "apparent" aerodynamic shape of the body (e.g., St D » O(1), Erk 1997, Smith et al 1998, Amitay et al 2001, Honohan et al 2000, Glezer et al 2005. The global flow characteristics are typically modified with active flow control by issuing a jet through a high aspect ratio orifice along the body surface.…”

Section: Technical Backgroundmentioning

confidence: 99%

Unsteady Aerodynamic Flow Control of Moving Platforms

Glezer¹

2014

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Modification of lifting body aerodynamics using synthetic jet actuators

Cited by 164 publications

References 15 publications

Numerical Characterisation of Active Drag and Lift Control for a Circular Cylinder in Cross-Flow

Numerical Characterisation of Active Drag and Lift Control for a Circular Cylinder in Cross-Flow

Experimental and Computational Study on Separation Control Performance of Synthetic Jets with Circular Exit

Unsteady Aerodynamic Flow Control of Moving Platforms

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