A. The aircraft starts its cruise at seal level under best range conditions using the cruise...

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A. The aircraft starts its cruise at seal level under best range conditions using the cruise climb flight regime. It has a cruise fuel weight of 5,000 lb and a tsfc of 0.85 lb/h/lb. 1. Calculate the airspeed (mph) and range (miles) 2. Calculate the corresponding flight path angle in degrees. 3. Calculate the mileage (or instantaneous range) at the end of flight (mi/gal) D. A turbojet aircraft has a thrust-to-aircraft weight ratio of 0.1 and a thrust-to-engine weight ratio of 0.4. The structural weight fraction is 0.43 and the design fuel weight fraction is 0.22. If the payload is 80,000lb, find the payload weight fraction and the gross weight of the aircraft. Aircraft A Aircraft B Aircraft C Gross Weight 24,000 lb 14,500 N 210,000 lb Wing area 600 ft 2 6.12 m 2,500 ft Maximum thrust 6,000 lb 3,400 N 40,000 lb C DD 0.02 0.03 0.016 K 0.056 0.09 0.045 M. DR 0.72 0.72 0.82 C, 1.8 1.22 1.9 max NB: 1 ft = 0.3048 meters 1 mile = 5280 ft A. The aircraft starts its cruise at seal level under best range conditions using the cruise climb flight regime. It has a cruise fuel weight of 5,000 lb and a tsfc of 0.85 lb/h/lb. 1. Calculate the airspeed (mph) and range (miles) 2. Calculate the corresponding flight path angle in degrees. 3. Calculate the mileage (or instantaneous range) at the end of flight (mi/gal) D. A turbojet aircraft has a thrust-to-aircraft weight ratio of 0.1 and a thrust-to-engine weight ratio of 0.4. The structural weight fraction is 0.43 and the design fuel weight fraction is 0.22. If the payload is 80,000lb, find the payload weight fraction and the gross weight of the aircraft. Aircraft A Aircraft B Aircraft C Gross Weight 24,000 lb 14,500 N 210,000 lb Wing area 600 ft 2 6.12 m 2,500 ft Maximum thrust 6,000 lb 3,400 N 40,000 lb C DD 0.02 0.03 0.016 K 0.056 0.09 0.045 M. DR 0.72 0.72 0.82 C, 1.8 1.22 1.9 max NB: 1 ft = 0.3048 meters 1 mile = 5280 ft

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