The thesis “Comparative Analysis of Aircraft Wing Profiles” explores how different airfoil shapes affect lift and airflow using 2D simulations in MATLAB’s CFDTool. It focuses on the NACA 2412 airfoil tested at various angles of attack to study aerodynamic behavior and stall. The research is grounded in aerodynamic theory, including Bernoulli’s principle and wing geometry. Results showed varying lift performance among profiles and highlighted the limits of simplified simulations. Despite using basic tools, the study offers useful insights for future aerodynamic design and analysis.