[NSRCA-discussion] CG

[Scott Smith]

>>  Also, the wing and stab area should include the ailerons and elevators,
respectively.

When calculating wing/stab area, are you also including the area occupied by
the fuselage?  Such that an 18" wing root on a 6" wide body would add 108 sq
in to the panel area.
  -----Original Message-----
  From: nsrca-discussion-bounces at lists.nsrca.org
[mailto:nsrca-discussion-bounces at lists.nsrca.org]On Behalf Of Ron Van Putte
  Sent: Monday, May 29, 2006 6:07 PM
  To: NSRCA Mailing List
  Subject: Re: [NSRCA-discussion] CG




  On May 29, 2006, at 4:40 PM, Nat Penton wrote:


    The following formula was presented by noted British modeller Gordon
Whitehead in How To Make Scale Models Fly ( 1980 ??). I have been using it
over 20 years and find it dead on for pattern:
    CG (from LE MAC) = MAC/6 + 0.25x As/Aw M
    As - area stab Aw - area wing
    M - moment arm, ac to ac
    It is easy to use the graphic method to find the wing MAC. You can guess
at the stab MAC and be close enough.
    The formula works on anything from a tailess to a Quickie.


  Nat - I haven't compared the formula with the one I developed more than 40
years ago, but I think yours would be better understood if you use some
parentheses:


  CG (from LE MAC) = MAC/6 + 0.25x (As/Aw) M


  Also, the wing and stab area should include the ailerons and elevators,
respectively.




  Ron Van Putte

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