A military Jet aircraft if fitted with a fixed convergent-divergent afterburner with an exit-to-throat area ratio...

 

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A military Jet aircraft if fitted with a fixed convergent-divergent afterburner with an exit-to-throat area ratio of 2. The reservoir pressure are 101kPa and 288K, respectively. Calculate the Mach number, pressure, and temperature at both the throat and the exit for the cases where: (a) The flow is supersonic at the exit. (9 marks) (b) The flow is subsonic throughout the entire nozzle except at the throat, where M = 1. (9 marks) Assume the exit pressure is 973kPa as a result of the aircraft operating at altitude. (c) Calculate the Mach numbers at the throat and the exit. (7 marks) A military Jet aircraft if fitted with a fixed convergent-divergent afterburner with an exit-to-throat area ratio of 2. The reservoir pressure are 101kPa and 288K, respectively. Calculate the Mach number, pressure, and temperature at both the throat and the exit for the cases where: (a) The flow is supersonic at the exit. (9 marks) (b) The flow is subsonic throughout the entire nozzle except at the throat, where M = 1. (9 marks) Assume the exit pressure is 973kPa as a result of the aircraft operating at altitude. (c) Calculate the Mach numbers at the throat and the exit. (7 marks)

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The question youve presented involves the application of the principles of gas dynamics specifically those related to the flow of air through a convergentdivergent CD nozzle which is an essential comp... View the full answer