wing span b = 22 m wing area S = 50 m Oswald efficiency factor e = 0.8 maximum lift coefficient CL max maximum load factor thrust specific fuel consumption TSFC = 1.4 nmax = 3 0.6 kN/(kN h) maximum fuel mass mmf = 5,100 kg maximum payload mass mmp = 1,250 kg Zero Lift drag coefficient = 0.017 Empty aeroplane mass = 8600 Total max take-off weight = 14300 Calculate the maximum range of the aeroplane if it carries a payload of 200 kg. Also calculate the associated amount of fuel and the time required to complete the journey. Base your calculations on the following assumptions: The aeroplane cruises at 10,000 m altitude. 500 kg of fuel are required for the climb. During the climb, which lasts for 20 minutes, the distance covered is 100 km. Ignore the descent phase.