Nick & Mart.
Nick, there is no argument with what you say. However, your statement
"that the profile power is too high when a big blade is hovered" got the neurons firing.
The theme of this thread relates to forward speed and a craft with twin main-rotors. The three of us, and others on the forum, have an interest in what might be called the next generation rotorcraft. Therefore ...
During cruise, all future rotorcraft will likely slow their rotors. This reduced rotational speed strongly suggests that their chords will probably be increased over that of current rotorcraft. During hover, a larger chord will increase the profile drag (as you say), however, a slowing of the rotor speed during hover will reduce the profile drag. This raises the question as to which will win the tug-of-war over the profile drag.
The following results are calculated from Prouty's 'Combined Momentum and Blade Element Theory with Empirical Corrections', in the chapter 'Aerodynamics of Hovering Flight'. It consists of incremental changes to the blade's chord and then finding the RRPMs that give matching thrusts.
The constants are: Pitch = 8º. Taper = 0º. Twist = 0º. Blades = 4. Profile = NACA 0012
Interestingly, after excluding the first column, the horsepowers do not vary much. This appears to imply that on high-speed rotorcraft, wide chord blades will not be detrimental to hover.
Dave