You need to be a bit more precise - a wing will always stall at the same AoA as long as it's in the same configuration. Changing the configuration will change the properties of the airfoil and alter the lift and drag coefficients and - curves.
but in general simple flaps increase wing loading, decrease stall speed, decrease limit loads...however the basic airfoil lift characteristics are not changed so the Clmax point of the wing [not the flap section] changes..you have more lift at lower speeds,..hence changes in the loading with effective camber increase is independent of aoa...I'm not sure what this conversation is truly about..
...the above is true look it up
edit:
it's important for the new generation to see the possibilites...although nothing to do with flaps--just an excuse to put GK in..
