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winksaville / py-airfoils

Some airfoil sections as Python arrays
MIT License
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Question: which airfoils are best for testing of offset algorithms #1

Open adam-urbanczyk opened 3 years ago

adam-urbanczyk commented 3 years ago

I'm working on https://github.com/CadQuery/cadquery/pull/694 and I'd like to test if the resulting splines allow to calculate an 2D offset curve. Which of the profiles should I use for testing?

winksaville commented 3 years ago

I'd try all of them, the first two are easiest as they are symmetrical. The next two are thin cambered "typical" airfoils. The last one is "tricky" as it's trailing edge is reflexed (kicking up).

NACA airfoil

The NACA four-digit wing sections define the profile by [2]

  1. First digit describing maximum camber as percentage of the chord.
  2. Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
  3. Last two digits describing maximum thickness of the airfoil as percent of the chord.[3]

naca0005 symmetrical airfoils 5% thickness naca0020 symmetrical airfoils 20% thickness naca5305 thin cambered foil that 5=% thickness at 30%

goe63 thin cambered foil mh49 Reflexed airfoil