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Naca 2412 airfoil series#

The formula used to calculate the mean camber line is:

Naca 2412 airfoil series#

The simplest asymmetric foils are the NACA 4-digit series foils, which use the same formula as that used to generate the 00xx symmetric foils, but with the line of mean camber bent. The camber line is shown in red, and the thickness – or the symmetrical airfoil 0012 – is shown in purple. 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. 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.