question archive 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
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
Subject:MathPrice: Bought3
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?
