Just chipping in with my 2c...
There is a lot of talk of AoA, specific angles, and initiation of stall recovery here. The question is, are we discussing stall of an aerofoil or an aircraft?
As above, a fairly standard aerofoil section will stall at or around 16 degrees AoA, this is repeatable and well understood.
Once the aerofoil is attached to an aircraft, and that aircraft is in motion all factors change. Its also of paramount importance to understand that the AoA of the wing, is completely different to the aircraft 'pitch', they are two mutually exclusive states.
Once you suss out the concept of the Relative Air Flow, you'll find all this to be much more clear. Best of luck!