The S6063 airfoil has a nice stall margin above the top Cl in the low drag bucket.
The top of the low drag bucket is a Cl of about 0.4 but the airfoil doesn't stall until Cl of 0.8. You can calculate the bank angle for Cl 0.4 at speed and have a fairly reliable visual indication to the pilot of the G's to pull while staying within the low drag bucket. This behavior is typical of thin airfoils. This avoids the transient and other detrimental effects of pulling too high a coefficient of lift.