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ETOPS_example_2011

# ETOPS_example_2011 - CEE 5614 Analysis of Air...

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Virginia Tech - Air Transportation Systems Laboratory CEE 5614 Analysis of Air Transportation Extended Over Water Operations (ETOPS) Example 1

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Virginia Tech - Air Transportation Systems Laboratory Problem Description Use the large twin-engine transport aircraft performance file provided in the Matlab files for CEE 5614 (http://128.173.204.63/courses/cee5614/ matlab_files_cee5614.html to answer the following questions. The aircraft is cruising at FL 350 and Mach 0.82 over the Atlantic Ocean enroute from Santo Domingo (SDQ), Dominican Republic to Madrid (Spain) as shown in Figure 1. The aircraft has a mass of 320,000 kg at the departure airport (SDQ). The takeoff mass is comprised of the following: Operating empty mass = 145,000 kg Fuel weight onboard= 115,000 kg Payload = 60,000 kg (300 passengers + 30,000 kg of belly cargo in LD3 containers) The pilot files a flight plan and requests Flight Level 350 for the cruise portion the flight The aircraft flies to a waypoint position located 1,700 nm from SDQ (see Figure 1) when an engine failure is detected by the crew. The crew initiates a gradual descent at 290 knots IAS and declares an emergency with Oceanic ATC) and diverts to the best alternate airport. The distances from the point of engine failure to all alternate airports filed in the flight plan are shown in Table 2. Assume ISA conditions in the analysis. 77
Virginia Tech - Air Transportation Systems Laboratory ETOPS Flight (SDQ-LEMD) 78

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Virginia Tech - Air Transportation Systems Laboratory Calculation of Climb Profile (Using Matlab Code) 4 107 nm to reach the Top of Climb Point 17.65 minutes to reach the TOC point. Initial Mass = 320,000 kg
Virginia Tech - Air Transportation Systems Laboratory Fuel Burn to the Point of Engine Failure 5 dR dt = V T = D = 1 2 ρ V 2 SC d dW dt TSFC ( T ) = TSFC ( 1 2 ρ V 2 SC d ) V tas = 295m/s(0.82) = 241.9 m/s The system of two simultaneous equations can be solved using Matlab. Note that during the cruise phase, the speed of the aircraft does not change. The aircraft cruises at Mach 0.82 at 35,000 feet. Assuming ISA conditions, the speed of sound (a) at 10,671 meters is 295 m/s. The true airspeed is:

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Virginia Tech - Air Transportation Systems Laboratory Fuel Burn at TOC Point 6 W TOC = W takeoff FW c lim b W TOC = (320,000 kg)(9.81 m/s 2 ) (6,405kg)((9.81 m/s 2 ) W TOC = 3,076,400 N = 313,595kg The drag at cruise at the Top of Climb point would be: V tas = 241.9 m/s C l = 0.6412 (dim) C d = C do + C di = 0.0189 + 0.0175 = 0.0364 (dim) D = 178,300 N
Virginia Tech - Air Transportation Systems Laboratory Fuel Burn at TOC Point 7 The fuel consumption at the TOC point is then, dW dt = TSFC ( D ) = TSFC ( T ) = (1.6 e 4 N/N/s)*(178300 N) dW dt = 28.53N/s The aircraft takes 12,196 seconds (3.39 hours) to

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