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 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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