Wing Optimisation for a Hypothetical Electric General Aviation Aircraft
Python-driven optimisation workflow selecting from 170+ NACA airfoils and refining a 3D wing in XFLR5, reaching a cruise glide ratio of 31.46.
XFLR5
Experimental Aerodynamics of a NACA 4412 Airfoil: Wind Tunnel Validation
Low-speed wind tunnel testing of 2D and 3D NACA 4412 configurations, validating experimental data against XFLR5 predictions and published literature.
Aerodynamic Analysis and Optimisation of NACA Airfoils with XFLR5/XFOIL
Systematic study of how Reynolds number, Mach number, thickness, and camber drive airfoil performance, automated into a reusable Python evaluation workflow.