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.
Airfoil nomenclature. Image in the public domain, via Wikimedia Commons.
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
>>> 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
pip install airfoils
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