Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil

In this paper, 3D numerical simulations have been carried out to enhance the understanding of a flow over a passive control device composed of micro cylinder with, d/c = 1.34% placed in the vicinity of NACA0012 aerofoil wing, by means of γ–Reθt transition sensitive turbulence model meant to predict...

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Autores principales:	Larabi Abderrahim, Pereira Michael, Ravelet Florent, Azzam Tarik, Oualli Hamid, Menfoukh Laiche, Bakir Farid
Formato:	article
Lenguaje:	EN FR
Publicado:	EDP Sciences 2021
Materias:	Environmental sciences GE1-350
Acceso en línea:	https://doaj.org/article/edaf51e8ac174a0ca6f9e3e4c85fa136
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spelling	oai:doaj.org-article:edaf51e8ac174a0ca6f9e3e4c85fa1362021-11-12T11:44:34ZNumerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil2267-124210.1051/e3sconf/202132101011https://doaj.org/article/edaf51e8ac174a0ca6f9e3e4c85fa1362021-01-01T00:00:00Zhttps://www.e3s-conferences.org/articles/e3sconf/pdf/2021/97/e3sconf_icchmt2021_01011.pdfhttps://doaj.org/toc/2267-1242In this paper, 3D numerical simulations have been carried out to enhance the understanding of a flow over a passive control device composed of micro cylinder with, d/c = 1.34% placed in the vicinity of NACA0012 aerofoil wing, by means of γ–Reθt transition sensitive turbulence model meant to predict the separation induced by transition achieved for aerofoils operating at moderate Reynolds number (Re = 4.45×105). Results show that the separation of the boundary layer has been eliminated by the passive static vortex generator at stall regime due to the injection of free-stream momentum to the boundary layer. The early transition to turbulent state overcomes the local flow deceleration of an adverse pressure gradient and remains sticked to the wall the boundary layer. Furthermore, the wing aerodynamic performance are improved as drag is reduced and lift is enhanced which is straight forward linked to the lift to drag ratio gain that varies from 22.68% to 134.17% at post stall angles of attack.Larabi AbderrahimPereira MichaelRavelet FlorentAzzam TarikOualli HamidMenfoukh LaicheBakir FaridEDP SciencesarticleEnvironmental sciencesGE1-350ENFRE3S Web of Conferences, Vol 321, p 01011 (2021)
institution	DOAJ
collection	DOAJ
language	EN FR
topic	Environmental sciences GE1-350
spellingShingle	Environmental sciences GE1-350 Larabi Abderrahim Pereira Michael Ravelet Florent Azzam Tarik Oualli Hamid Menfoukh Laiche Bakir Farid Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
description	In this paper, 3D numerical simulations have been carried out to enhance the understanding of a flow over a passive control device composed of micro cylinder with, d/c = 1.34% placed in the vicinity of NACA0012 aerofoil wing, by means of γ–Reθt transition sensitive turbulence model meant to predict the separation induced by transition achieved for aerofoils operating at moderate Reynolds number (Re = 4.45×105). Results show that the separation of the boundary layer has been eliminated by the passive static vortex generator at stall regime due to the injection of free-stream momentum to the boundary layer. The early transition to turbulent state overcomes the local flow deceleration of an adverse pressure gradient and remains sticked to the wall the boundary layer. Furthermore, the wing aerodynamic performance are improved as drag is reduced and lift is enhanced which is straight forward linked to the lift to drag ratio gain that varies from 22.68% to 134.17% at post stall angles of attack.
format	article
author	Larabi Abderrahim Pereira Michael Ravelet Florent Azzam Tarik Oualli Hamid Menfoukh Laiche Bakir Farid
author_facet	Larabi Abderrahim Pereira Michael Ravelet Florent Azzam Tarik Oualli Hamid Menfoukh Laiche Bakir Farid
author_sort	Larabi Abderrahim
title	Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
title_short	Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
title_full	Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
title_fullStr	Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
title_full_unstemmed	Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
title_sort	numerical study on the effect of an off-surface micro-rod vortex generator placed upstream naca0012 aerofoil
publisher	EDP Sciences
publishDate	2021
url	https://doaj.org/article/edaf51e8ac174a0ca6f9e3e4c85fa136
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Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil

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