Aircraft A Aircraft B Aircraft C W Gross Weight 90,000 6 900,000 N 150,000 lb S Wing Area 1,500 ft 140 m 2500 ft Tra Maximum Thrust 25,000 lb 180,000 N 35,000 lb CDO 0.024 0.018 0.02 K 0,06 0.057 0.050 MDR CL max 0.85 0.83 0.82 1.8 1.8 1.9 NB: 1 ft-0.3048 meters 1 mile =5280 ft 1 gallon of fuel-6.75lb Question 1: Aircraft A (6 points) The Aircraft has a cruise fuel weight ratio of 0.3 and a tsfc of 0.9/h. The aircraft is starting its cruise at 25,000ft altitude under best range conditions at constant altitude, constant lift coefficient flight regime. Calculate the airspeeds at the beginning of cruise (mph). 1. Calculate the range (miles) and flight time (h). 2. 3. Calculate the thrust required to fly under these conditions (at the beginning of cruise). Is there enough thrust available to fly under these conditions? (Hint: calculate max thrust at that altitude) Question 2: Aircraft B (6 points) 1. Calculate the minimum absolute ceiling altitude for this aircraft (in meters). Calculate the corresponding velocity (km/h) at this altitude. 2. 3. Is this speed attainable? Justify. Question 3: Aircraft C (8 points) Aircraft B cruises at an altitude of 35,000ft. It has a cruise fuel weight 35,000lb and a tsfc of 0.87/h. It is flying at 500 mph at constant altitude, constant velocity. 1. Find the instantaneous range at the beginning and the end of flight (miles/gallons). 2. What is the range (miles) and flight time (h) under these conditions)? 3. How could you improve the distance this aircraft can fly with the same initial speed, initial altitude and cruise fuel weight fraction? Explain your answer (calculate improved range).