Buffalo Wings Documentation
Buffalo Wings is a Python geometry library for building airfoil and wing models from aerodynamic definitions. Its public airfoil API is designed as an expansive airfoil creation library that supports analytic NACA families, additional analytic shapes, point-defined airfoils, and file-backed airfoil sources. It is designed to support interactive design workflows, visualization tools, and downstream analysis or meshing pipelines.
Note
This project is under development and the API might change between releases.
Start Here
If you are new to the project, start with the examples page for working airfoil and wing scripts built on the public API. The airfoil subsystem is currently the most mature part of the project, while the wing subsystem is still evolving. If you want to understand the breadth of supported airfoil creation workflows, the Airfoil API Guide is a good early stop after the examples page.
New users should begin with Examples.
Airfoil-focused users should continue with Airfoil API Guide.
API-oriented users should go to Library Interface.
Contributors should start with Developer Resources.
Project Focus
The public API is centered on buffalo_wings.airfoil and buffalo_wings.wing.
Shared low-level foundations such as numeric typing, numeric normalization,
and structured diagnostics come from buffalo_core.
The project is being developed as both a usable Python library and a geometry foundation for future GUI-based airfoil and wing design tools.
Buffalo Wings is not intended to be a general-purpose CAD system.