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

Article dans une revue avec comité de lecture
Author
LARABI, Abderrahim
ccPEREIRA, Michaël
ccRAVELET, Florent
1003528 Laboratoire d'Ingénierie des Fluides et des Systèmes Énergétiques [LIFSE]
AZZAM, Tarik
OUALLI, Hamid
242513 École Militaire Polytechnique [Alger] [EMP]
MENFOUKH, Laiche
ccBAKIR, Farid

URI
http://hdl.handle.net/10985/21380
DOI
10.1051/e3sconf/202132101011
Date
2021
Journal
E3S Web of Conferences

Abstract

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.

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