5. The mission profile for a 4-engine jet aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to an altitude of 20000 ft followed by a cruise distance of R₁ nm at 350 kts, climb to an altitude of 35000 ft, followed by a cruise distance of R2 nm at 450 kts descent to 10000ft followed by one hour loiter and flight to an alternate airport at R3 nm distance both at 250 kts, descent to landing approach condition followed by the final landing, taxi and shutdown. The total distance during the cruise segments and flight to an alternate airport is restricted to a maximum of 5100 nm. Based on the existing manufacturers' data you may use the information provided in Table QA-1. L/D cruise at 20000 ft altitude L/D cruise at 35000 ft altitude 18 20 L/D at 10000 ft altitude (loiter and flight to an alternate airport) C;: Specific Fuel Consumption at cruise segments C;: Specific Fuel Consumption during loiter and flight to an alternate airport Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown Table QA1-1 16 0.43 lbs/hr/lbs 0.50 lbs/hr/lbs 0.992 0.996 0.996 0.992 0.996 0.992 No provisions are made for the reserved fuel or any trapped oil and fuel. The aircraft carries 200 people (including pilots and the cabin crew) at 175 lbs each and 90 lbs baggage each. You are given that during the cruise segment at 20000 ft the aircraft weight has been reduced by 18903.6 lbs. The wing of the aircraft has an area of 3000 ft² with an aspect ratio of 10.0. Additionally, the drag equation for the aircraft at its clean condition is given as: Ср = 0.0228 + CZ пае a- Sketch the mission profile with clear annotations and numbering. b- Determine the gross take-off weight of the aircraft

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Transcribed Image Text:5. The mission profile for a 4-engine jet aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to an altitude of 20000 ft followed by a cruise distance of R₁ nm at 350 kts, climb to an altitude of 35000 ft, followed by a cruise distance of R2 nm at 450 kts descent to 10000ft followed by one hour loiter and flight to an alternate airport at R3 nm distance both at 250 kts, descent to landing approach condition followed by the final landing, taxi and shutdown. The total distance during the cruise segments and flight to an alternate airport is restricted to a maximum of 5100 nm. Based on the existing manufacturers' data you may use the information provided in Table QA-1. L/D cruise at 20000 ft altitude L/D cruise at 35000 ft altitude 18 20 L/D at 10000 ft altitude (loiter and flight to an alternate airport) C;: Specific Fuel Consumption at cruise segments C;: Specific Fuel Consumption during loiter and flight to an alternate airport Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown Table QA1-1 16 0.43 lbs/hr/lbs 0.50 lbs/hr/lbs 0.992 0.996 0.996 0.992 0.996 0.992 No provisions are made for the reserved fuel or any trapped oil and fuel. The aircraft carries 200 people (including pilots and the cabin crew) at 175 lbs each and 90 lbs baggage each. You are given that during the cruise segment at 20000 ft the aircraft weight has been reduced by 18903.6 lbs. The wing of the aircraft has an area of 3000 ft² with an aspect ratio of 10.0. Additionally, the drag equation for the aircraft at its clean condition is given as: Ср = 0.0228 + CZ пае a- Sketch the mission profile with clear annotations and numbering. b- Determine the gross take-off weight of the aircraft

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