index.rst

Welcome to 's documentation!

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.

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

user_guide/installation user_guide/detailed_user_guide

references

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CHANGELOG

dev_doc/modules_main

Licence information

is developed at Airinnova AB, Stockholm.

Authors

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