An airfoil of surface area 0.1 m2 is tested for lift L m a wind tunnel. (Conditions can be considered as incompressible flow.) At an angle of attack of 5°, with standard air of density 1.22 kg/m3, at a speed of 30 m/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°?

An airfoil of surface area 0.1 m2 is tested for lift L m a wind tunnel

1.	An airfoil of surface area 0.1 m2 is tested for lift L m a wind tunnel. (Conditions can be considered as incompressible flow.) At an angle of attack of 5°, with standard air of density 1.22 kg/m3, at a speed of 30 m/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°?
A.	0.572 and 700 kgf
B.	0.603 and 700 kgf
C.	0.572 and 570 kef
D.	0.603 and 570 kef
Answer» B. 0.603 and 700 kgf

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