Pstaney,
Typically an airfoil experiences airflow separation by 25-30% chord, to some degree. So-called laminar airfoils experience it around 50%. A properly designed airfoil (which opens a very wide range of possibility in interpretation) shouldn't be experiencing any "aileron snatch" at CLmax. None.
Lowering the aileron will increase the angle of attack by increasing the angle of the chord line. Remember the chordline runs from the leading edge to the tailing edge, and lowering the trailing edge also lowers the chord line, or increases the angle of incidence...airflow remaining relatively unchanged in the free airstrea, angle of attack is therefore increased.
At the same time, you're also changing camber by lowering the aileron, which alters the coeficient of lift, too. CLmax will occur differently for that wing station.
Raising the aileron, generally speaking, decreases lift and also alters the coefficient of lift, generally decreasing it, and also decreasing drag.
How these affect an airplane really depends on the specific airplane. Applying aileron close to a stall may be helpful or hurtful in roll control, depending on the specific aerodynamics of the aircraft in question.