Thread: Discussion boundary layer thickness
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Old Sep 30, 2012, 02:00 PM
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Thanks for your cal. DPATE.

I made some cal. to find Cd at 200mph, with a average core length of just about 1 feet I found that re would be 1.800.000 at this point the airfoil has a Cd at 0.0038 (according to Profili).

The area is roughly 2.7 Sq feet on one side so I guess it has to be multiple by two...right?

If my cal. are correct then D (drag) would ending op being 2.14 for the model. But what dose this number tell me?
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Last edited by frank40; Oct 01, 2012 at 11:45 AM.
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