Motivation for this project is to help the engineers predict the 'Drag coefficient' and 'Lift coefficient' of their NACA 4 digit airfoils without running a physical test or a CFD simulation
Input variables:
- Angle of attack
- Maximum thickness of the airfoil
- Chord at maximum thickness
- Maximum camber of the airfoil
- Chord at maximum thickness
- Reynolds number
Target variables
- Lift coefficient
- Drag coefficient
Data source Airfoil data is obtained from airfoiltools website by web scraping Data source