Numerical Investigation on Flow Separation Control of Low Reynolds Number Sinusoidal Aerofoils
Ibrahim, Imran H.
New, Tze How
Date of Issue2016
46th AIAA Fluid Dynamics Conference
School of Mechanical and Aerospace Engineering
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.
NACA 634-021 aerofoil
© 2016 AIAA. This is the author created version of a work that has been peer reviewed and accepted for publication by 46th AIAA Fluid Dynamics Conference, AIAA. It incorporates referee’s comments but changes resulting from the publishing process, such as copyediting, structural formatting, may not be reflected in this document. The published version is available at: [http://dx.doi.org/10.2514/6.2016-3949].