I'm obviously missing some thing here. I thought Cl(max) was a function of the particular airfoil eg NACA 2410 a little over 2.4 at a Reynolds 6X10^6. I thought angle of attack was the sole key, forgetting about the rate of change of angle of attack and it's effect on Cl(max). My Abbott & Doenhoff seemingly makes no mention of CoG having any effect. Confused.
What are the aerodynamic reasons behind the phenomena? Thanks folks.