Having read FAA's PHAK chapter 6, I have a question about propeller which has the same angle of incidence from the hub to the tip.
Below is from the page 6-5 of PHAK
A propeller blade designed with the same angle of incidence throughout its entire length would be inefficient because as airspeed increases in flight, the portion near the hub would have a negative angle of attack while the blade tip would be stalled.
Stalling occurs only when critical AOA has exceeded. Does the AOA of propeller increases as the airspeed of the airplane increases? I can't understand. Could someone help me understanding this?