This project is a comprehensive suite for designing and optimizing 4-digit NACA airfoils. Born to meet various aerodynamic needs, the project is now organized into three main modules:
- inhouse_potential_optimizer: The core of the project. It uses a potential flow solver (Source-Vortex Panel Method) developed entirely in-house to optimize and analyze airfoil geometry extremely fast, without any external dependencies.
- xfoil_viscous_optimizer: The code that interfaces with the XFOIL executable to perform optimization taking into account viscosity and aerodynamic drag.
- validation_inhouse_vs_xfoil: The environment dedicated to comparing and mathematically validating the results obtained by our in-house potential solver against XFOIL viscous data.
- _Original_projects: Legacy code and original Matlab scripts (kept for reference).
Each folder contains its own README with usage instructions. To get started, we recommend trying out the inhouse_potential_optimizer!