CG Effect on Range/Airspeed
In main wing/tailplane configured FW aircraft, CG at rearward edge of envelope is a factor which decreasing total drag and therefore increasing range. I am interested to know if a given CG position would do the same in a helicopter configured with main rotor and tail rotor.
Is this so? If so, which CG position would yield the least drag and therefore increase fuel efficiency (and thus range): Forward CG? Mid-Range CG? or Aft CG? Please cite any references or data sources. Thank You.