Context & Justification
The aerodynamic design of airfoils for high-altitude operations presents particular challenges: low air density reduces generated lift and requires increasing flight speed or angle of attack, affecting overall aircraft efficiency. UAVs operating in the Ecuadorian highlands, at altitudes between 2,500 and 4,500 m.a.s.l., require specially optimized profiles for these conditions.
This project combines parametric design tools, computational aerodynamic simulation (CFD), and additive manufacturing to develop and validate airfoils with lift-to-drag ratios superior to conventional standards under low Reynolds number conditions, characteristic of high-altitude operations.
Main Research Goal
Specific Scopes
- Conduct a comparative study of existing airfoils (NACA, Eppler, Selig) under low Reynolds conditions and altitudes of 2,500 to 4,500 m.a.s.l. using two-dimensional simulation.
- Design a parametric airfoil optimized using multi-objective optimization algorithms (NSGA-II or similar) with aerodynamic and structural cost functions.
- Validate the selected profile through three-dimensional CFD simulation and low-speed wind tunnel tests at EPN's laboratory.
- Manufacture wing prototypes by 3D printing with PETG/fiber composite materials and evaluate structural resistance under real aerodynamic loads.
Research Products
Comparative aerodynamic database of candidate profiles under high-altitude operating conditions, with parametric sensitivity analysis.
Optimized airfoil with documented geometry (coordinates and parametric equations) and validated through CFD simulation with open-source and commercial software.
Physical prototype manufactured by additive manufacturing with structural resistance tests and experimental comparison with numerical data.
Technical article with optimization and validation results, targeted for presentation at a national or international aeronautics conference.