Originally Posted by
arismount
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.
Gentlemen, I started this thread. With all due respect, discussion is beginning to drift to controllable elevators, tailplanes, etc.
That is not the question I have...to restate, does CG position have anything to do with extended range or increase airspeed in a main rotor/tail rotor configured helicopter and if so, what CG position is most favorable for decreased total drag / increased airspeed / increased fuel efficiency ("max range")?
Please address this question, with references to data if at all possible.
Thanks in advance to The Community for your consideration.