E3S Web Conf.
Volume 321, 2021XIII International Conference on Computational Heat, Mass and Momentum Transfer (ICCHMT 2021)
|Number of page(s)||6|
|Published online||11 November 2021|
Numerical Study on the Effect of an Off-Surface Micro-Rod Vortex Generator Placed Upstream NACA0012 Aerofoil
Fluid Mechanics Laboratory, Ecole Militaire Polytechnique, BP 17 Bordj El Bahri, Algiers, 16111, Algeria
2 Arts et Metiers Institute of Technology, CNAM, LIFSE, HESAM University, F-75013 Paris, France
* Corresponding author: email@example.com
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.
© The Authors, published by EDP Sciences, 2021
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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