MATLAB AERODYNAMIC ANALYSIS

This project investigates the aerodynamic characteristics of two commonly studied NACA 4-series airfoils, NACA 4415 and NACA 2411, using an inviscid vortex panel method. Surface pressure distributions, velocity distributions, lift coefficients, pitching moments, and streamline visualizations were generated across a range of angles of attack from –4° to 12°. The analysis provides insight into the influence of camber and thickness on aerodynamic performance. The results demonstrate that the more highly cambered NACA 4415 exhibits a higher lift coefficient at zero angle of attack, a more pronounced suction peak, and a more negative quarter-chord pitching moment compared to the NACA 2411. Streamline and velocity-contour plots further illustrate the flow behavior around each airfoil. This report summarizes the methodology, numerical implementation, results, and comparative aerodynamic trends between the two airfoils.