Numerical Investigation on Flow Separation Control of Low Reynolds Number Sinusoidal Aerofoils

Ibrahim, I.H. , Joy, J. and New, T.N. (2016) Numerical Investigation on Flow Separation Control of Low Reynolds Number Sinusoidal Aerofoils. In: 46th AIAA Fluid Dynamics Conference, AIAA AVIATION Forum, Washington, DC, USA, 13-17 June 2016, ISBN 9781624104367 (doi: 10.2514/6.2016-3949)

152279.pdf - Accepted Version



The paper presents a computational analysis of the characteristics of a NACA 634- 021 aerofoil incorporated with sinusoidal leading-edge protuberances at Re = 14,000. The protuberances are characterized by an amplitude and wavelength of 12% and 50% of the aerofoil chord length respectively. An unsteady Reynolds Average Navier Stokes (RANS) analysis of the full-span aerofoils was carried out using Transition SST (Shear Stress Transport) turbulence model across five different angles-of-attack (AOA). Comparisons with previous experimental results reported good qualitative agreements in terms of flow separation when the aerofoils are pitched at higher AOAs. Results presented here comprised of near-wall flow visualizations of the flow separation bubble at the peaks and troughs of the protuberances. Additionally, results indicate that the aerofoil with leading-edge protuberances displayed distinctive wall shear streamline and iso-contour characteristics at different span-wise positions. This implies that even at a low Reynolds number, implementations of these leading-edge protuberances could have positive or adverse effects on flow separation.

Item Type:Conference Proceedings
Glasgow Author(s) Enlighten ID:Ibrahim, Dr Imran
Authors: Ibrahim, I.H., Joy, J., and New, T.N.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Copyright Holders:Copyright © 2016 American Institute of Aeronautics and Astronautics, Inc.
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher.

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