A turbojet target drone aircraft is flying at M=0.8 at sea level in std. ISA conditions. a. Determine the aircraft's thrust given that the jet pipe exit nozzle is choked and has an exit static pressure of 166783 Pa and an exit static temperature of 484°C. The jet pipe exit nozzle has a diameter of 250mm. b. Determine the propulsive efficiency of the turbojet aircraft. c. Determine the specific fuel consumption if Air/Fuel Ratio is 71:1.
A turbojet target drone aircraft is flying at M=0.8 at sea level in std. ISA conditions. a. Determine the aircraft's thrust given that the jet pipe exit nozzle is choked and has an exit static pressure of 166783 Pa and an exit static temperature of 484°C. The jet pipe exit nozzle has a diameter of 250mm. b. Determine the propulsive efficiency of the turbojet aircraft. c. Determine the specific fuel consumption if Air/Fuel Ratio is 71:1.
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Transcribed Image Text:A turbojet target drone aircraft is flying at M=0.8 at sea level in std. ISA conditions.
a. Determine the aircraft's thrust given that the jet pipe exit nozzle is choked and has an
exit static pressure of 166783 Pa and an exit static temperature of 484°C. The jet pipe
exit nozzle has a diameter of 250mm.
b. Determine the propulsive efficiency of the turbojet aircraft.
c. Determine the specific fuel consumption if Air/Fuel Ratio is 71:1.
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