Airfoil Modifier

Y-axis stretch coefficient (0.1 - 5.0)
X-axis stretch coefficient (0.1 - 5.0)
Adds a third Z coordinate to each airfoil point (Z = 0.0)
📐 Detailed calculation formulas Study the math and physics of calculations
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Modification results

Configure modification parameters and click "Modify airfoil". Default file doc/PW51.dat will be used, or upload your own airfoil coordinates file.

Project created by ai.oxteam.me