An airfoil of surface area 0.1 m² is tested for lift L in a wind tunnel. (Conditions can be considered as incompressible flow.) At an angle of attack of 5 °, with standard air density 1.22 kg/m³, at a speed of 30m/sec, the lift is
measured to be 3.2 kgf. What is the lift coefficient? For a prototype wing of area 10 m², what is the approximate lift at an air speed of 160 kmph at the same angle of attack of 5 °?