rotorcraft 'g' limit
sir
for a given rotorcraft weight, main rotor diameter, chord, airfoil, rotor rpm what may be the 'g' capability the rotor can sustain(steady or transient) during maneuver(pull up/turn/wing over...). Is there any empirical formula to calculate rotor capability in terms of 'g' for a single main rotor and tail rotor helicopter configuration. Suppose if there is no empirical formula as such then for a given weight of 3.2Tonnes, hingeless rotor what may be the rotor capability in terms of 'g' for similar contemporary helicopter weight class. Am talking about aerodynamic 'g' capability of rotor.
Thanks in advance
sincerely
Jagannath