PDAS home > Contents > NACA Airfoil > Thickness > 4-Digit (modified)
Public Domain Aeronautical Software (PDAS)

For example, a 23015-64 airfoil would have a maximum thickness of 15 per cent, a 230 mean line, a leading edge radius corresponding to an index of 6, and the position of maximum thickness would be at 40 per cent chord.

The thickness distribution is given by the following equation ahead of the maximum thickness:

y = A0 sqrt(x) + A1 x + A2 x**2 + A3 x**3

where ** denotes exponentiation, (t/c) is the maximum thickness to chord ratio of the airfoil, x is the position as fraction of chord, and y is the half-thickness as fraction of chord.

and by the following equation from maximum thickness to trailing edge:

y = D0 + D1(1-x) + D2 (1-x)**2 + D3 (1-x)**3

There is a special page that describes the details of the calculation of A0, A1, A2, A3, D0, D1, D2, D3 from the values of thickness, position of maximum thickness, and leading edge radius that are specified by the user.

PDAS home > Contents > NACA Airfoil > Thickness > 4-Digit (modified)
Public Domain Aeronautical Software (PDAS)