[NSRCA-discussion] CG

[Ron Van Putte]

On May 29, 2006, at 6:09 PM, Scott Smith wrote:

> >>  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.

In my calculations I do include the area occupied by the fuselage.  I  
assume the calculation by Nat does as well, but I don't speak for him.

Ron Van Putte
> -----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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