AnFI you contradict yourself -
what matters is where it is when it reaches the peek AoA - that will be where stall starts
that is 'peak AoA' btw and not true
Then you say
2ndly if a rotor stalls it will flap down which increases the AoA
so the peak AoA is after the blade stalls - do get your 'further along' theory right.
As for
not really true tho' - that's not really how helicopters work
do please explain what happens to a blade/wing at a certain AoA if the TAS reduces over that blade/wing - you believe it doesn't experience a loss of lift and then descend then
