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A 200 seated jet aircraft is cruising at Mach No. of 0.79 with the following given data at 10 km altitude. Range = 4,000 km Endurance = 60 minutes Maximum (L/D) = 17 SFC during Cruise = 14.1 mg/(Ns) SFC during Loiter = 11.3 mg/(Ns) Density = 0.413 kg/cu.m Pressure = 26,000 N/sq.m Empirical constants for empty weight ratio, a = 0.92 and C = –0.06 Payload = 500 kg Passenger mass = 65 kg/passenger Luggage = 20 kg/passenger a) Draw mission segment. b) Calculate weight of the aircraft c) Calculate empty weight d) Calculate fuel weight

A 200 seated jet aircraft is cruising at Mach No. of 0.79 with the following given data at 10 km altitude. Range = 4,000 km Endurance = 60 minutes Maximum (L/D) = 17 SFC during Cruise = 14.1 mg/(Ns) SFC during Loiter = 11.3 mg/(Ns) Density = 0.413 kg/cu.m Pressure = 26,000 N/sq.m Empirical constants for empty weight ratio, a = 0.92 and C = –0.06 Payload = 500 kg Passenger mass = 65 kg/passenger Luggage = 20 kg/passenger a) Draw mission segment. b) Calculate weight of the aircraft c) Calculate empty weight d) Calculate fuel weight

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A 200 seated jet aircraft is cruising at Mach No. of 0.79 with the following given data at
10 km altitude.

Range = 4,000 km
Endurance = 60 minutes
Maximum (L/D) = 17
SFC during Cruise = 14.1 mg/(Ns)
SFC during Loiter = 11.3 mg/(Ns)
Density = 0.413 kg/cu.m
Pressure = 26,000 N/sq.m
Empirical constants for empty weight ratio, a = 0.92 and C = –0.06
Payload = 500 kg
Passenger mass = 65 kg/passenger
Luggage = 20 kg/passenger

a) Draw mission segment.

b) Calculate weight of the aircraft

c) Calculate empty weight

d) Calculate fuel weight

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