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'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.
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.





RE: Transition Reynold's Number Range
Dont forget that there are areas of greater resistance to airflow around wheels struts and any non-conforming pods/bays holding them if they close for flight.
If this is too simple an answer then youre stuck doing the math again.
RE: Transition Reynold's Number Range
RE = Inertia Forces/Viscous Forces
ht
http://www2.eng.cam.ac.uk/~tph/L6.pdf
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For text book see “Aerodynamics or Naval Aviators” page 54-60.
Chears!
RE: Transition Reynold's Number Range