The equations for the 6-series camber lines are rather complicated and there is little value in displaying them here.

They may be found

- on p.8 of NASA TM 4741
- as Eq. 4.26 and 4.27 on p.74 of Abbott and von Doenhoff, Theory of Wing Sections
- as Eq. 6 on p.264 of NACA Report 824

6-series camber lines are specified with a parameter *a*,
where *a* is a fraction of chord.
The intent is to provide a uniform loading from the leading edge to
the station *x=a* and a loading that decreases linearly to zero thereafter.