Yeah it is Sierra Sue..you got it right.

http://en.wikipedia.org/wiki/Drag_coefficient

I am buzzled...how do you add up all the drag...if the wing is laminar flow type and plate the drag coefficient is 0.001...what is it if the foil is 12% thick ( 0.0047-0.0045 in AR-5 ) ?

AR-5 pages Carmichael say the drag coefficient of the plane was 0.016...when he says the wing drag area is 0.248 sq ft ( in the summary )...does he mean flat plate equivalent area ? Because the frontal area of the wing is at least 15 x that area. http://www.ar-5.com/condrag94.html

How much in % is the interference drag generally in a smooth plane ( 4.1% in AR-5 and induced drag 3.6 %) ?

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Seems to me that in the wing he is using wetted area and multiply that with coeffiecient and in the fuse and multiply that area by coefficient.