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Jan4-04, 06:34 PM
P: 2
Hi Enigma,

Thanks for your welcome and reply.

The wing is swept, tapered, constant airfoil and untwisted. I recently came across an equation in Datcom (Section 4.1.4) and also used in Roskam's "Airplane Design" Part 6 which relates the Cm of the airfoil to the Cm of the wing, given aspect ratio and sweep.

Would anyone know about the equation and how it is derived? I don't think it's from lifting-line theory which doesn't give info about force distributions in the chordwise direction.