i am pretty clear about why a higher camber would increase Clmax, but critical aoa.
one of the resources i read the graphic shows a greater chamber near the leading edge will increase Cl at different aoa and Clmax, a greater that of trailing edge will increase both Clmax and crtical aoa.(i can't post a link due to the web, i'm in china, really sorry for that)
as far as i know camber would increase the gradient which leads to a wilder separation, that's going to make the airfoil easier stall.
but on the other hand, may be a greater camber would increase the performance of aircrafts at larger aoa? like a leading edge flap?
i have went through a lot of conversations about camber-Cl curve relations, they are basically about Clmax.