The equation for a cambered 4-digit NACA airfoil The leading edge approximates a cylinder with a radius of: to −0.1036) will result in the smallest change to the overall shape of the airfoil. If a zero-thickness trailing edge is required, for example for computational work, one of the coefficients should be modified such that they sum to zero.
Note that in this equation, at ( x/ c) = 1 (the trailing edge of the airfoil), the thickness is not quite zero.
PLANE AIRFOIL SERIES
Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. The NACA four-digit wing sections define the profile by: 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. 1.2 The equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.