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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…

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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 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 9×10^6, what are CL and CD for the flying wing?