airfoils

Airfoils is a small Python library for object-oriented airfoil modelling. The library provides tools to easily instantiate airfoil objects and to query geometric information. An airfoil object is defined by upper and a lower surface coordinates.

Example — Airfoil nomenclature. Image in the public domain, via Wikimedia Commons.

Features

Airfoil generation with a NACA-4 series definition
Import from files
- Full support for airfoils from the UIUC Airfoil Coordinates Database
Interpolation or computation of airfoil geometry parameters
- Upper and lower surface coordinates
- Camber line coordinates
- Chord line coordinates (TODO)
- Thickness distribution (TODO)
- Maximum thickness (TODO)
Linear interpolation between two different airfoils (MorphAirfoil)
Plotting of airfoils

Example

>>> from airfoils import Airfoil
>>> foil = Airfoil.NACA4('4812')
>>> foil.plot()

>>> foil.y_upper(x=0.5)
array(0.13085448)
>>> foil.y_lower(x=[0.2, 0.6, 0.85])
array([0.00217557, 0.02562315, 0.01451318])
>>> foil.camber_line(x=0.5)
0.07789290253609385

Installation

pip install airfoils

Documentation

https://airfoils.readthedocs.io/

License

License: Apache-2.0

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