Question2 The mission profile for a jet driven aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to the cruise altitude of 35000 ft, descend to 10000 ft, one hour loiter at this altitude at 60% of the cruise speed, flight at loiter speed and altitude to an alternate airport (100 nm), descend to landing approach condition followed by the final landing, taxi and shutdown. The cruise Mach number is 0.8. 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 lb each and 90 lb baggage each. This aircraft has a wing area of 2000 ft² L/D at cruise L/D at 10000ft flight Table Q2 20 16 0.43 lb/hr/lb 0.50 lb/hr/lb C: Specific Fuel Consumption at cruise: C: Specific Fuel Consumption at 10000 ft flight: Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown 0.992 0.996 0.996 0.996 0.992 0.992 Question 2 continues on the next page Question 2 continued b) This aircraft is required to satisfy the following requirement based on standard day at sea level condition: 1) 1) FAR25.119, AEO, CGR>0.032, landing gear down, landing flap, take-off on all engines, maximum landing weight at 1.3 VSL Your calculation should be based on the landing weight of 0.85 WTO, C(Lmax) Landing = 2.50, the wing loading of 100 lb/ft2, the wing aspect ratio of 10 and an average Oswald efficiency corresponding to the landing configuration. You may also ignore the effect of the compressibility on the drag characteristics of the aircraft. Take-off distance of no more than 6000 ft at sea level and C(max) To = 2.2. What should be the relationship between thrust loading and wing loading to satisfy this requirement? =

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:Question2 The mission profile for a jet driven aircraft consists of the following segments: engine start and warm-up, taxi, take-off, climb to the cruise altitude of 35000 ft, descend to 10000 ft, one hour loiter at this altitude at 60% of the cruise speed, flight at loiter speed and altitude to an alternate airport (100 nm), descend to landing approach condition followed by the final landing, taxi and shutdown. The cruise Mach number is 0.8. 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 lb each and 90 lb baggage each. This aircraft has a wing area of 2000 ft² L/D at cruise L/D at 10000ft flight Table Q2 20 16 0.43 lb/hr/lb 0.50 lb/hr/lb C: Specific Fuel Consumption at cruise: C: Specific Fuel Consumption at 10000 ft flight: Weight ratios Engine Start and warm-up Taxi Take-off Climb Descent Landing, taxi and shutdown 0.992 0.996 0.996 0.996 0.992 0.992 Question 2 continues on the next page