Comparative Study of Aerodynamic Characteristics of Standard and Dimpled NACA 0012 Airfoil

This study analyzes the aerodynamic performance of a NACA 0012 airfoil with dimples on its upper surface, comparing it to the standard configuration. Using the Navier-Stokes equations, Blasius solutions, the k-ε turbulence model, and ANSYS Fluent, steady-state incompressible flow was simulated at 25 m/s across angles of attack from -20° to +20°. Results show the standard airfoil performs well at the low Reynolds number and lower angle of attack. The inward dimple airfoil reduces drag at negative angles, while the outward dimple airfoil enhances lift at higher positive angles. Shear stress analysis reveals laminar flow on flat plates and turbulent boundary layers on the modified airfoils. Pressure, velocity, and shear stress contours illustrate the impact of dimple placement on flow dynamics, demonstrating its potential for enhancing aerodynamic efficiency by delaying flow separation and optimizing lift-to-drag ratios.