Designers,

Thanks to Brett I now am armed with the tail area ration formula it is.

Tail Area X Tail Moment / Wing area X Wing Chord (at root I suppose?)

Where Tail Moment = CG to the 1/4 Chord of the tail group

(ie, Stab and Elevator) actually CG should also be the wing 1/4 Chord

I believe, but Brett uses CG for simplicity.

Lets see: My Stab/Elevator combo as I have laid it out on paper has

a root total chord of 6.75 inches and a tip chord of 5.0 inches. The span

totals 26 inches. so the tail group area = 6.75 + 5.0 / 2 X 26

which is; 152.75 sq in. My wing area will be 663 sq inches and the

chord flaps included is 12.75 inches the moment arm from the quarter

chord of the wing will be 25 inches. Lets plug these figures into the

formula and see if we can get something over .4 for an answer.

152.75 X 25 / 663 X 12.75 = .4517493

Yes that gives some over the .4 goal! I suppose we can add a little

more area or moment arm if we can balance it with the engine and

other items in the nose!

Thanks for all the suggestions so far. Now we need to come up with

what the fuselage and vertical stabilizer will look like. I already

know that DD suggested determining the side area of the Infinity

then squaring it? Naw, I don't think so. Maybe just a little less than

the Infinity. Too much side area can be as bad as, or worse than

too little I would think! Ted, what do you think regarding side area?

Jim Pollock javascript:replaceText('

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Tongue