Distributed forcing flow control in the wake of a blunt trailing edge profiled body using plasma actuators

Naghib-Lahouti, Arash; Hangan, Horia; Lavoie, Philippe

doi:10.1063/1.4914406

Cited by 22 publications

(4 citation statements)

References 42 publications

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“…Furthermore, the aforementioned undesirable increase in the turbulence energy content of the flow is decreased due to the presence of a weaker shear layer downstream of the proposed 3D surface treatments, especially for the S-type configuration. This is in agreement with the surface pressure Finally, the drag coefficient ( ) for the clean and treated flat plates can be estimated using a momentum balance approach using the boundary layer velocity data [6,36]. The drag coefficient can be estimated using,…”

Section: B Boundary Layer Velocity Fieldsupporting

confidence: 63%

Novel Three-Dimensional Surface Treatments for Trailing-Edge Noise Reduction

2019

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The present study is concerned with the experimental investigation of novel complex surface treatments as a passive trailing edge noise control technique. The proposed novel three-dimensional surface treatments, composed of a combination of finlets with different spacings and patterns, have shown better aeroacoustic performance than the standard twodimensional treatments in terms of the reduction in the surface pressure power spectral density, the spanwise length-scale, eddy convection velocity and the trailing edge noise. Furthermore, the boundary layer flow measurements downstream of the surface treatments has provided some insight into the mechanisms through which three-dimensional surface treatments affect the flow structures, which can help improve the performance of such passive techniques for the suppression airfoil noise at source. The aerodynamic performance of the plates fitted with different surface treatments is also examined using the boundary layer velocity information. The results from this fundamental study can lead to the development of new generations of quieter airfoils with unconventional surface treatments. Nomenclature c = flat plate chord, m = drag coefficient

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Section: B Boundary Layer Velocity Fieldsupporting

confidence: 63%

Novel Three-Dimensional Surface Treatments for Trailing-Edge Noise Reduction

2019

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“…Active Flow Control Field Flow separation control [132][133][134] Wake control [135] Aircraft noise reduction [136,137] Modification of velocity fluctuations [138][139][140] Drag reduction [94] Lift coefficient enhancement [103,141] Flow boundary layer modification [142] Turbulence reduction [143,144] Heat Transfer Field Film cooling efficiency enhancement [145,146] Surface cooling [147] Deicing and anti-icing [28,148,149] Ice sensing [30,111] 3.1. Thermal Effects Induced by Dielectric Barrier Discharge Plasma Actuators Although most of the initial studies mainly considered the aerodynamic plasma effect and neglected the heat dissipation phenomenon, we now know that a large percentage of the power applied to the DBD plasma device is dissipated in the form of heat.…”

Section: Dbd Plasma Actuators' Applicationsmentioning

confidence: 99%

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

et al. 2022

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Ice accretion is a common issue on aircraft flying in cold climate conditions. The ice accumulation on aircraft surfaces disturbs the adjacent airflow field, increases the drag, and significantly reduces the aircraft’s aerodynamic performance. It also increases the weight of the aircraft and causes the failure of critical components in some situations, leading to premature aerodynamic stall and loss of control and lift. With this in mind, several authors have begun to study the thermal effects of plasma actuators for icing control and mitigation, considering both aeronautical and wind energy applications. Although this is a recent topic, several studies have already been performed, and it is clear this topic has attracted the attention of several research groups. Considering the importance and potential of using dielectric barrier discharge (DBD) plasma actuators for ice mitigation, we aim to present in this paper the first review on this topic, summarizing all the information reported in the literature about three major subtopics: thermal effects induced by DBD plasma actuators, plasma actuators’ ability in deicing and ice formation prevention, and ice detection capability of DBD plasma actuators. An overview of the characteristics of these devices is performed and conclusions are drawn regarding recent developments in the application of plasma actuators for icing mitigation purposes.

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“…In fact, while the wake structure downstream of cylinders has received significant attention, this is not the case for the wake of streamlined bodies 25 and even less so for FB airfoils at high Reynolds numbers. 26 However, secondary instabilities in the wake of bluff bodies can be used to implement efficient flow control strategies [27][28][29][30] and their knowledge is crucial. These are knowledge gaps that need to be covered, since FB profiles are now commonly used in wind turbine design.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the three-dimensional flow past a flatback wind turbine airfoil at high angles of attack

Μανωλέσος

Papadakis

2021

Physics of Fluids

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Flatback airfoils are airfoils with a blunt trailing edge. They are currently commonly used in the inboard part of large wind turbine blades, as they offer a number of aerodynamic, structural, and aeroelastic benefits. However, the flow past them at high angles of attack (AoA) has received relatively little attention until now. This is important because they usually operate at high AoA at the inboard part of Wind Turbine blades. The present investigation uses Reynolds averaged Navier-Stokes (RANS) and hybrid RANS þ large eddy simulation predictions to analyze the flow in question. The numerical results are validated against previously published wind tunnel experiments. The analysis reveals that to successfully simulate this flow, the spanwise extent of the computational domain is crucial, more so than the selection of the modeling approach. Additionally, a low-drag regime observed at angles of attack before stall is identified and analyzed in detail. Finally, the complex interaction between the three-dimensional separated flow beyond maximum lift (stall cells) with the vortex shedding from the blunt trailing edge is revealed.

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Distributed forcing flow control in the wake of a blunt trailing edge profiled body using plasma actuators

Cited by 22 publications

References 42 publications

Novel Three-Dimensional Surface Treatments for Trailing-Edge Noise Reduction

Novel Three-Dimensional Surface Treatments for Trailing-Edge Noise Reduction

Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation

Investigation of the three-dimensional flow past a flatback wind turbine airfoil at high angles of attack

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