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AIRFOIL DATABASE SERIES

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. t is the maximum thickness as a fraction of the chord (so 100 t gives the last two digits in the NACA 4-digit denomination).

is the half thickness at a given value of x (centerline to surface), and.

x is the position along the chord from 0 to c,.

The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is: 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.

AIRFOIL DATABASE 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.