An airplane has a total mass of 35,000 kg and a wing planform area of 65 m². The airplane is cruising at 10,000 m altitude with a velocity of 1100 km/h. The density of air on cruising altitude is 0.414 kg/m³. The lift coefficient of this airplane at the cruising altitude is

(a) 0.273 

(b) 0.290 

(c) 0.456 

(d) 0.874 

(e) 1.22