A pure jet engine propels an aircraft at 520 mph at an altitude where the are 3.5 psia and -46 °F, respectively. The compressor pressure ratio is 12.4 and the mass flow rate at pressure and temperature the engine inlet is 70 lbm/sec. Operational considerations dictate that the maximum temperature of the working fluid entering the turbine be restricted to 1800 °F. Use cold air-standard assumptions. Calculate the a) Velocity of b) Thrust produced by the engine (Ibf) gas flow at the nozzle exit c) Propulsive efficiency of the cycle

A pure jet engine propels an aircraft at 520 mph at an altitude where the are 3.5 psia and -46 °F, respectively. The compressor pressure ratio is 12.4 and the mass flow rate at pressure and temperature the engine inlet is 70 lbm/sec. Operational considerations dictate that the maximum temperature of the working fluid entering the turbine be restricted to 1800 °F. Use cold air-standard assumptions. Calculate the a) Velocity of b) Thrust produced by the engine (Ibf) gas flow at the nozzle exit c) Propulsive efficiency of the cycle

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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مراد جبار فرحان In a gas turbine engine (A, = 2.85 A2, p1 = 1.14 p2, p1 = 100.5 kPa, T, = 11 °C, v1 = 107 m-s1, V2 = 785 m-s", A, = 2.4 m?), calculate the thrust force. %3D %3D ===
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