Flow Control on a Wing Section Through the Implementation of the SDBD Plasma Actuator

R. A. Bernal-Orozco; A. Arias-Montano; O. Huerta-Chávez

doi:10.1007/978-3-030-45402-9_15

Flow Control on a Wing Section Through the Implementation of the SDBD Plasma Actuator

R. A. Bernal-Orozco, A. Arias-Montano, O. Huerta-Chávez

Escuela Superior de Ingeniería Mecánica y Eléctrica (ESIME), Unidad Ticomán

Research output: Contribution to journal › Article › peer-review

Abstract

This work presents a Computational Fluid Dynamics (CFD) wind flow analysis technique applied to a Wing Section using a two-dimensional Reynolds-Averaged Navier-Stokes Method. The behavior of the flow has been studied from different angles of attack of the aerodynamic section until the angle of stall is found. An active flow control by means of the SDBD plasma actuator is implemented numerically, through body force source terms in the Navier-Stokes equations to re-attach the boundary layer of the flow. Then, altering the position and frequency of the SDBD plasma actuator results in the delay of the stall beyond 16^∘ and an increase of lift with reduction of the drag for new critical angles of stall.

Original language	English
Pages (from-to)	147-158
Number of pages	12
Journal	Mechanisms and Machine Science
Volume	86
DOIs	https://doi.org/10.1007/978-3-030-45402-9_15
State	Published - 2020

Keywords

Airfoil with plasma actuator
Dielectric barrier discharge
Flow-control
RANS
SDBD

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10.1007/978-3-030-45402-9_15

Cite this

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title = "Flow Control on a Wing Section Through the Implementation of the SDBD Plasma Actuator",

abstract = "This work presents a Computational Fluid Dynamics (CFD) wind flow analysis technique applied to a Wing Section using a two-dimensional Reynolds-Averaged Navier-Stokes Method. The behavior of the flow has been studied from different angles of attack of the aerodynamic section until the angle of stall is found. An active flow control by means of the SDBD plasma actuator is implemented numerically, through body force source terms in the Navier-Stokes equations to re-attach the boundary layer of the flow. Then, altering the position and frequency of the SDBD plasma actuator results in the delay of the stall beyond 16∘ and an increase of lift with reduction of the drag for new critical angles of stall.",

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author = "Bernal-Orozco, {R. A.} and A. Arias-Montano and O. Huerta-Ch{\'a}vez",

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T1 - Flow Control on a Wing Section Through the Implementation of the SDBD Plasma Actuator

AU - Bernal-Orozco, R. A.

AU - Arias-Montano, A.

AU - Huerta-Chávez, O.

PY - 2020

Y1 - 2020

N2 - This work presents a Computational Fluid Dynamics (CFD) wind flow analysis technique applied to a Wing Section using a two-dimensional Reynolds-Averaged Navier-Stokes Method. The behavior of the flow has been studied from different angles of attack of the aerodynamic section until the angle of stall is found. An active flow control by means of the SDBD plasma actuator is implemented numerically, through body force source terms in the Navier-Stokes equations to re-attach the boundary layer of the flow. Then, altering the position and frequency of the SDBD plasma actuator results in the delay of the stall beyond 16∘ and an increase of lift with reduction of the drag for new critical angles of stall.

AB - This work presents a Computational Fluid Dynamics (CFD) wind flow analysis technique applied to a Wing Section using a two-dimensional Reynolds-Averaged Navier-Stokes Method. The behavior of the flow has been studied from different angles of attack of the aerodynamic section until the angle of stall is found. An active flow control by means of the SDBD plasma actuator is implemented numerically, through body force source terms in the Navier-Stokes equations to re-attach the boundary layer of the flow. Then, altering the position and frequency of the SDBD plasma actuator results in the delay of the stall beyond 16∘ and an increase of lift with reduction of the drag for new critical angles of stall.

KW - Airfoil with plasma actuator

KW - Dielectric barrier discharge

KW - Flow-control

KW - RANS

KW - SDBD

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DO - 10.1007/978-3-030-45402-9_15

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SP - 147

EP - 158

JO - Mechanisms and Machine Science

JF - Mechanisms and Machine Science

ER -

Flow Control on a Wing Section Through the Implementation of the SDBD Plasma Actuator

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