CFD Analysis of NACA 0015 Airfoil with High-Lift Devices

Conducted an in-depth CFD analysis of a NACA 0015 airfoil with leading-edge slat and trailing-edge flap configurations. Key Achievements: • Performed steady-state and transient simulations using Spalart-Allmaras turbulence model • Analyzed flow characteristics at 0° and 12° angles of attack • Concluded that slats help improve aircraft stability at AOA 12° which is optimal for takeoff and landing Skills: Altair Hypermesh