Improve distribution of points along airfoils #2
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This commit changes the x-distribution of points along the airfoil from using a constant step size to using a variable step size as explained near the bottom of the following page: http://airfoiltools.com/airfoil/naca4digit?MNaca4DigitForm%5Bcamber%5D=0&MNaca4DigitForm%5Bposition%5D=0&MNaca4DigitForm%5Bthick%5D=12&MNaca4DigitForm%5BnumPoints%5D=81&MNaca4DigitForm%5BcosSpace%5D=0&MNaca4DigitForm%5BcosSpace%5D=1&MNaca4DigitForm%5BcloseTe%5D=0&MNaca4DigitForm%5BcloseTe%5D=1&yt0=Plo The leading edge is resolved significantly better when using this distribution.
This commit adds a dependency but should theoretically be a better way to get the value of pi.
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I'd also be happy to make the same changes to the AirfoilMesh script as well if you are willing to merge this PR. |
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Guys, I was using this and noticed that the point distribution, especially near the leading edge, when using this script (and the AirfoilMesh script as well) was lacking. I came across this link describing (near the bottom of the page) a better way to distribute points and I implemented it.
See attached screen shots for a demonstration of this improvement.