In most helicopters....does the thrust produced by a full application of right pedal(American direction of rotation) equal or exceed the amount of torque (turning force) of the Main Rotor System in a hovering aircraft?
Question being....if a full right pedal application equals or exceeds the Turning Moment of the Main Rotor system....one could test various techniques to control the spinning of the aircraft.
I guess if one were brave enough....one could apply full right pedal at a Hover and attempt to fly away and establish some sort of controlled flight with the nose of the aircraft yawed from the direction of flight.
In flight, we know if one reduces the MR RPM to the bottom of the Green Arc (Power On Limit) the resulting yaw is minimized or removed.
You CFS Rotor Scholars might answer the question about the amount of Torque applied to the Rotor System when RPM is reduced....does the Torque decrease with the decrease in RPM even though more pitch is applied to the Rotor? In my younger days I would offer my own calculations but I am well beyond that in my old age. CRS (Can't Remember Squat) has firmly set in and prevents me from throwing out the answer.
Any thoughts on this?(The flying parts...not my CRS!)
Brother John Dixon or Professor Lappos would be great sources of thinking on this!