This situation needs a bit more detail before it can be answered - how or what is going to give the trade off of cyclic response to improved rotor energy?
Years ago Bell did a project with a Jet Ranger with increased inertia in the blades (quite a bit of increased weight). The result showed that for this machine, there was no HV curve- that is, no combination of airspeed and height that would prevent a safe landing. But this would only be over a suitable landing area, of course.
So what is the mechanism that is going to give us this increased benefit - need to know that before the question can be answered.
And for Part 29 helicopters (more than 7,000lbs) with more than 10 seats, the HV curve is a limitation, so unless you can eliminate the HV curve, you won't help those operators.
More info please!!!