3 G-CCTG Press esc to exit full screen A finite wing on an experimental aircraft has an aspect ratio of 10. The wing area is 20 m. The wing has a NACA 4415 airfoil with a span efficiency factor of .85. The wing is flying at an angle of attack of 3. Determine the three-dimensional lift and drag coefficients, i.e., CL and CD. Utilize appendix D for the two-dimensional, airfoil data. Also determine the lift and drag generated if the aircraft is cruising at 70 m/s and an altitude of 2,000 m under standard conditions. Solve the problem in the International system of units. ZOOM +