# How does camber affect on critical aoa?

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.

many thanks

• @Raketenolli I suggest you go to airfoil tools. 0012, 2412, and 4412 indeed showed that increasing camber increases stall AoA, not surprisingly more so at lower Reynolds numbers. So, please take a time out, and maybe come up with a decent answer to contribute to this thread. (Reynolds over 10 × 10$^6$ may be interesting, but hey, that might be why airliners know when to fold 'em). Aug 24, 2022 at 22:01