NACA 4 Series Airfoils (symmetrical)


The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word “NACA”. The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties. Parametric equation for the generation of the symmetrical NACA 4-series airfoils relates the half thickness of the airfoil to the chord length and the maximum thickness as a fraction of the chord.

Related formulas


yt is the half thickness at a given value of x (centerline to surface) (dimensionless)
tis the maximum thickness as a fraction of the chord (so 100 t gives the last two digits in the NACA 4-digit denomination). (dimensionless)
cis the chord length (dimensionless)
x is the position along the chord from 0 to c (dimensionless)