Originally Posted by
jagannath
Am talking about aerodynamic 'g' capability of rotor.
Such a calculation would be very complicated. It would have to take into account so many variables such as rotor blade section both chord wise and spanwise, blade twisting under load, blade area, rotor speed, air speed, air density and mass.
In practical terms I suspect that unlike a fixed-wing, rather than having a "break" at the stall, attempting to pull increasing amounts of g becomes harder and harder since the rotor system tends to mush, caused I presume by some part of the disc becoming stalled whilst others remain flying, and perhaps an increased amount of blade twist from aerodynamic load. Thus there is a massive increase in drag as the limit of lift is approached.