Airfoil Generator (NACA)
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Generate NACA 4-digit airfoil coordinates from the standard camber and thickness equations.
4-digit
points
NACA 2412 from normalized chord equations
The dashed curve is the mean camber line. Upper and lower surfaces are offset normal to that line by the NACA thickness distribution.
Max camber
2.0%
first digit
Camber location
40%
second digit
Max thickness
12.0%
last two digits
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.