NACA 4 Series Airfoils (symmetrical)
Description
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 formulasVariables
| yt | is the half thickness at a given value of x (centerline to surface) (dimensionless) |
| 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). (dimensionless) |
| c | is the chord length (dimensionless) |
| x | is the position along the chord from 0 to c (dimensionless) |
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