An aircraft weighing 900 kN when empty has a wing area of 226 m2. It is to take off at velocity of 400 km/h and angle of attack 20°. Assume the airport is at 3500m above sea level. The wing has the characteristics of an airfoil shown in the figure below (CL vs a). What is (1) the allowable weight of the cargo and (in) induced drag coefficient if the wing span is 30m. (ii) the stall velocity The pressure variation in the atmosphere is given as: =p:(1-Bolt 6.5K Where R is the gas constant for air, B is the lapse rate = "T R=287 J/K/kg, subscript s=sea-level. Ps=101.325kPa 9.=9.81 m/s/s km Ts = 15°C Chord 10.45 90.40 Loefficiente 1.6 0.22 1.2 0.24 Druco 0.3 0.16 OH 04 00 ol 041 0 36 24 Angle of attack, a degrees