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Submitted by c13daniel.gieck on Tue, 2012-02-14 03:07
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ambilyaero on Mon, 12 Mar 2012
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Consider a flying-wing aircraft made using a NACA 2412 airfoil with a wing area of 250 ft ^2, a wing...
Consider a flying-wing aircraft made using a NACA 2412 airfoil with a wing area of 250 ft ^2, a wing span of 50 ft, and a span efficiency factor of 0.9. If the aircraft is flying at a 6 deg angle of attack and a Reynolds number of approximately 9x10^6, what are CL and CD for the flying wing?