Numerical Analysis and Optimization of Winglet Configurations for Aerodynamic Efficiency Enhancement Using CFD

Abstract

This dissertation examines the aerodynamic performance of the NACA 2412 airfoil using Computational Fluid Dynamics (CFD). It reviews the fundamentals of airfoil theory, including key airfoil families and aerodynamic principles such as lift, drag, pressure coefficient, and Reynolds number. The governing Navier–Stokes equations and the SST k–ω turbulence model are applied for numerical simulation due to their accuracy in turbulent flow prediction. CFD simulations were conducted at different velocities (10, 15, and 20 m/s) and angles of attack (0°, 5°, 10°, and 15°). The results show that increasing the angle of attack increases both lift and drag coefficients, with flow separation occurring at higher angles. Optimal aerodynamic performance is achieved at moderate angles of attack, confirming that CFD is an effective tool for analyzing airfoil behavior.