More than once I`ve read that the airfoil thickness contributes little to the lift in relation to the angle of attack and airfoil curvature and it (thickness) is more concerned with airfoil stall characteristics.

Could anyone prove it mathematically?

Thank you

More than once I`ve read that the airfoil thickness contributes little to the lift compared to the angle of attack and airfoil curvature and has more to do with airfoil stall characteristics.

Could anyone explain this, preferably mathematically?

Thank you