Lots of assumptions in play there. However, if you're going to say that, then wouldn't you have to include level flight as well?

Either one of those assumes the wing has an angle of incidence of zero in relation to the longitudinal axis (pitch reference) of the aircraft.

If the wing was mounted on the fuselage with a positive 2 degree angle of incidence, when it rotated to 5 degrees of pitch on takeoff roll, AOA would be 7.