A rectangular wing with a NACA 1412 airfoil section spans the test section of a wind tunnel. The test speed is 176 f/s. The wing is at an angle of attack of 4 degrees. The span of the airfoil is 3 ft, and the chord of the airfoil is 0.50 ft. Assume sea level conditions. Assume the Reynolds number is 9(10)^6. Solve the problem in British system of units. a) What is the lift being generated by the wing? b) What is the drag generated by the wing? c) What is the moment about the aerodynamics center?

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Given Airfoil sectionNACA 1412 Wing span b3 ft Wing chord c05 ft Airfoil area Sb c 15 ft Flow veloci... View the full answer