Objective
Team project (team of 5) investigating the aerodynamic behaviour of a NACA 4412 airfoil through low-speed wind tunnel testing, comparing two-dimensional (end-plated) and three-dimensional wing configurations.
Approach
- Tested across multiple Reynolds numbers and angles of attack, collecting surface pressure and force balance data.
- Applied aerodynamic data reduction techniques to extract lift, drag, pitching moment, aerodynamic centre, and induced drag.
- Cross-validated experimental results against XFLR5 predictions, theoretical thin-airfoil calculations, and published literature.
- Quantified the influence of 3D effects (finite span, induced drag) and support interference on measured performance versus the idealised 2D case.
Result
- Final grade: 87%
Why this project
This is the project where CFD/panel-method predictions stopped being theoretical for me — reconciling the gap between XFLR5’s 2D predictions and what we actually measured on a finite 3D wing (induced drag, support interference) gave me a much sharper feel for where simulation tools break down and why experimental validation matters in aerodynamic design.