Fixed sum airloads on an airfoil

[JLS]

My previous post was just plain wrong; formulas were for a
center of pressure under 1/3 chord, such as ironically
NACA 23000 series of airfoil.


For center of pressure over 1/3 chord the fixed sum
airloads on airfoil is as illustrated below.


The center of pressure at Cl 0.2 (0.717 chord) is
far to aft and over the wing chord that's make
the calculus at this point erroneous.


So if you have an idea for that (Cl 0.2 limit
and acceptable center of pressure/wing chord
ratio) you're welcome to share it.

This post "Fixed Sum Airloads on an airfoil" is for educational purposes only and may contain errors. Any attempt
to use the results for actual design purposes are done at the user's own risk.