posted on Jun, 28 2017 @ 08:20 AM
a reply to: JIMC5499
The main limiting factor on helicopter airspeed is actually retreating blade stall due to the retreating blade reaching it's critical angle of attack
and 'stalling' when on that side of the disc. This causes major dissymmetry of lift and the helicopter pitches up, slowing the airspeed and almost
naturally recovering itself.
Hypothetically in a situation where there are wings providing lift and pusher props providing thrust the main rotor's collective pitch could be
reduced to lessen the effect of retreating blade stall.