The wing camber formula depends on the specific airfoil shape being used. One common formula for camber line calculation is the NACA 4-digit series formula, which determines the camber line based on a series of parameters.
Where:
- is the camber line’s vertical position,
- is the maximum camber as a fraction of the chord length,
- p is the location of the maximum camber as a fraction of the chord length, and
- is the distance along the chord from the leading edge.