Q1. Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has an NACA 23012 aerofoil section and a chord of 0.3 m, a) calculate the lift, drag per unit span and the lift to drag ratio when the airflow pressure, temperature, velocity and viscosity are 1 atm, 303 K, 42 m/s, and 1.82 10-5 respectively. The angle of attack is 8. Use the presented data set to extract c, Ca. b) calculate the net skin-friction drag coefficient, the total skin-friction drag, and the total pressure drag force on the wing. Answers are available in Lecture 3 7 Moment coefficient, 3. Section at coefficient, e -1.2 1.6 3.6 32 28 2.4 201 1.6 1.2 -16 -8 0 Secrian angle of attack, de NACA 23012 Wing Bertion Moment coefficient, c 024 3020 Section drag coefficient, c DIB 012 008 16 24 -1.6 -12 -8 as position t We 30x10 241 036 6.0 241 .035 88 247 004 A 60 Standard roughness Section lift coefficient, NACA 23012 Wing Section (Continued) 1.2