Aerodynamic Performance of the NACA 63-012 Airfoil with Sinusoidal-Shaped Leading Edge at Low Air Velocity
Authors: Kunya BI, Aliyu AB, Salihu BM
This research work focused on numerical simulation of the effect of sinusoidal bumps (or tubercles) at the leading edge of an airfoil on efficiency using NACA 63-012 cross-section profiles. Two computational softwares (GAMBIT and FLUENT) were used. The GAMBIT was used for the modeling and meshing while the FLUENT was used for the simulation. Shear stress transport (k-omega or k-ω) and Spalart Allmaras (SA) turbulence models available in the simulation software were used. The characteristics investigated included flow separation (or stall), lift and drag, angle of attack, and bumps effect at low Reynolds number. The results show that bumps on the blade leading edge have advantage at higher angle of attack for both turbulence models.
Affiliations: Department of Mechanical Engineering, Federal Polytechnic Mubi, Adamawa State, Nigeria.
Keywords: Angle Of Attack, Lift Coefficient, Drag Coefficient, Bumps, Flow Separation
Published date: 2020/12/30