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Question: a boeing 7879 with a mass of 254 metric...

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. A Boeing 787-9 with a mass of 254 metric tons takes off from a 3 km long runway with a wing configured to provide Ci 1.7. The aircraft has a wing area of 377 m2, an aspect ratio of 9.69 and CDo-0.024. a) If the air density near the ground is 1.2 kg/m3, what is the minimum thrust in kN produced by each of its two Rolls-Royce Trent 900 engines during take-off? b) Estimate the downward velocity in m/s induced by the aircraft during takeoff. c) Estimate the minimum amount of fuel in metric tons required to fly 11000 km if the heat content of the fuel, H 40 MJ/kg and the efficiency of conversion of fuel energy to motive energy is 30%. Assume that the Lift to Drag ratio is 18. 2. An aircraft with mass, M, is cruising at its optimum speed, ve, at a height where is the air density is p. The friction drag coefficient is Coo, the wing area is A, the aspect ratio is ar, and the lift coefficient is CL. 1. Derive an expression for the cruising speed by minimizing the drag. Take the 2. 3. induced drag coefficient to be CITa,. Taking M-300 metric tons, A-350 m, CD0-0.018, ar-8, p-0.4 kg/m3, compute the cruising speed in km/h, and the associated thrust in kN. If the takeoff mass of the aircraft is 350 metric tons, and the aircraft is designed to travel 12000 km, what is minimum mass of fuel in metric tons should the aircraft carry? Take the engine efficiency to be 0.4 and the energy content of the fuel to be 40 MJ/kg 4. If the air density near the ground is 1.2 kg/m3, and Cu-1.5, what is the minimum thrust in kN required to take off from a runway 2 km in length.
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