CFD Analysis of NACA 2412 Airfoil With Winglets at Varying Cant Angles: A Comparative Study on Aerodynamic Performance

Abstract

The integration of winglets on aircraft wings has been widely recognized as an effective method to reduce induced drag and improve overall aerodynamic efficiency. This study presents a computational fluid dynamics (CFD) analysis of a NACA 2412 airfoil wing with and without winglets at varying cant angles of 30°, 45°, and 60°. The simulations were performed using a steady-state approach under subsonic flow conditions to evaluate key aerodynamic parameters such as lift coefficient (Cl), drag coefficient (Cd), and lift-to-drag ratio (L/D). The baseline configuration without winglets served as a reference for comparison. Results indicate that the inclusion of winglets significantly reduces induced drag, with the 45° cant angle providing the most favorable balance between lift enhancement and drag reduction. Flow visualization further highlights the suppression of wingtip vortices, contributing to improved aerodynamic efficiency. These findings underscore the potential of optimized winglet designs in enhancing aircraft performance and fuel efficiency. The study provides insights for future design considerations in both commercial and unmanned aerial vehicle applications.