[nabla9]

Roughly 80% of the lift is generated above the wing in typical aircraft. Angle of attack is part of it and not a counterargument.

As the angle of attack is increases, the point of minimum pressure moves forward and the size of the adverse pressure gradient increases.

btw. In most most airfoils zero angle of attack and zero lift axis differ. The wing generates lift even without the angle of attack. Chambered wings are exception to this.