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Transition Reynold's Number Range

Transition Reynold's Number Range

Transition Reynold's Number Range

(OP)
If you calculate the Reynold's number of the fuselage to be about 10^6 and the wings to be about 3e5 of a high-speed, small-scale aircraft, is it possible to have a higher profile drag on the wings than the fuselage?  I'm not sure if being on opposite sides of the critical Reynold's number would have a strong enough effect on drag.

I'd appreciate any help on the subject, and would love to get references with page numbers.  I've been using Hoerner's and Raymer's books, but I would like confirmation.

P.S. Will, thanks for the tip!

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