Just a couple

[Tinstaafl]

I took the AoA question to mean 'How is AoA controlled?', not 'Name all factors that affect AoA?'.

Hope that explains why I answered as I did.

Inbalance, AoA must increase in a level turn. Because the lift vector is tilted, to maintain altitude it must be increased. This is done by pitching the a/c nose up. This increases the AoA.

The resultant effect is to increase the total force the wing produces ie both lift and drag. The drag results in a negligible loss of speed at low angles of bank but is countered by adding more power/thrust at high AoB.

I think you're mistaking pitch attitude and/or no change in trim for a constant AoA.

jrs2,

Apart from devices that modify the wing's LE & TE, or alters the rigger's incidence, the relationship between chord line & pitch attitude is fixed.

What is of concern is the relationship between chord (or indirectly, pitch attitude) and relative airflow.

Using the relationship you mentioned ie Att. + Pwr. = Perf. and a level flight example:

All other factors being equal, at a given speed the a/c will require a certain power setting and a certain AoA (controlled by adjusting pitch attitude with elevator).

Hence the terms in the formula you quoted: Power and Attitude.

If you add power while attempting to maintain altitude you will have no choice but to use the elevator to lower the pitch attitude/AoA.

It's not the speed that is changing the AoA, but your choice to adjust pitch attitude to maintain a constant flight path.

If you don't change the pitch attitude the a/c will eventually stabilise in a climb at the same speed (near as an ASI shows). AoA will be slightly less than it was in level flight at that speed but the a/c is now in a different flight path with a different resolution of forces.