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formula for centre of gravity


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Paul - I've always used a method from the Aeromodeller Plans Handbook in the dim and distant -

(wing chord / 7), + ((3 X tailplane area X moment arm) / (8 X wing area))

if wing and tail are tapered, chord is at half span, moment arm is from 1/4 chord of wing to 1/4 chord of tail.

This gives a safe CG from the LE of the wing, at the mid point if tapered.

In practice it puts the CG at around 30 to 35% of the wing chord.

Graeme

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