Consider an NACA 0012 airfoil. NACA airfoil is a symmetric 4 digit airfoil. The chord is given as 520mm. Now, we need to know: 1. x - the distance along the chord from leading edge. 2. y - half thickness of aerofoil 3. t - max thickness as fraction of cord.

Max Camber (%) Max camber position (%) Thickness (%) Number of points Cosine spacing Close Trailing edge 0 12 200 First digit, 0 to 9.5% Second digit. 0 to 90% Third & fourth digit. 1 to 40% 20 to 200 Dat file NACA 0012 Airfoil M 0.0% P 1.000000 0.001260 0.999753 0. 001295 0.999013 0. 001398 0.997781 0.001571 0.996057 0.001812 0.993844 0.002120 0.991144 0.002496 0.987958 0.002937 0.984292 0.003443 Cosine or linear spacing Open or closed TE Plot Send to airfoil plotter Add to mparison Add to My airfoils NACA 4 digit airfoils in the database NESPRESSO NACA 0006 NACA 0008 NACA 0012 Max Camber (%) Max camber position (%) Thickness (%) Number of points Cosine spacing Close Trailing edge 0 12 200 First digit, 0 to 9.5% Second digit. 0 to 90% Third & fourth digit. 1 to 40% 20 to 200 Dat file NACA 0012 Airfoil M 0.0% P 1.000000 0.001260 0.999753 0. 001295 0.999013 0. 001398 0.997781 0.001571 0.996057 0.001812 0.993844 0.002120 0.991144 0.002496 0.987958 0.002937 0.984292 0.003443 Cosine or linear spacing Open or closed TE Plot Send to airfoil plotter Add to mparison Add to My airfoils NACA 4 digit airfoils in the database NESPRESSO NACA 0006 NACA 0008 NACA 0012