#5 DIGIT AIRFOIL GENERATOR GENERATOR#
#5 DIGIT AIRFOIL GENERATOR SERIES#
The following table presents the various camber line profile coefficients:įour- and five-digit series airfoils can be modified with a two-digit code preceded by a hyphen in the following sequence: The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is: y t = 5 t c , Plot of a NACA 0015 foil, generated from formula The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.Įquation for a symmetrical 4-digit NACA airfoil The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. įor example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.
The NACA four-digit wing sections define the profile by: