As far as RPM in the normal range is concerned >90, aft cyclic that raises the nose, when there's forward airspeed, will increase RPM, we all know that. Fun to play with (with due caution, of course), roll off the throttle and flare the helicopter, see how long you can maintain the RPM.
As far as increasing pitch goes, I was referring to the increase in pitch on one blade, the advancing blade, when aft cyclic is applied.
I've spent a couple hours sitting here trying to figure out a few things.
A. What is the angle of attack of the blades at full down collective, 60 knots forward speed and 80% RPM versus 104%
B. Could an aft cyclic stall the advancing blade? Lets say at full down, 60 knots, level attitude and 80% RRPM the AOA is 14 degrees. Add in two degrees to the advancing blade from the cyclic input and it would exceed a theoretical critical angle of attack of 16 degrees.
C. What factor does inflow/ROD play? You can't get 14 degrees of AOA on blades who's pitch is low without it.
D. Without a complete understanding of all the factors involved, such as what the air is actually doing over the span of a rotorblade when it stalls, it's really hard to figure this out!
My hats off to those aerodynamicists out there!
James