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oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J/kg-k. The nozzle has an exit to throat area ratio of Ae / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (a) Mass flow rate m for choked flow (b) Critical Mach numbers (c) Critical pressures

oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J/kg-k. The nozzle has an exit to throat area ratio of Ae / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (a) Mass flow rate m for choked flow (b) Critical Mach numbers (c) Critical pressures

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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Question 3.) An engine has an inlet stagnation condition of 300 bar and 4000 kelvin. Methane and liquid oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J/kg-k. The nozzle has an exit to throat area ratio of A₂ / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (a) Mass flow rate m for choked flow (b) Critical Mach numbers (c) Critical pressures
Transcribed Image Text:Question 3.) An engine has an inlet stagnation condition of 300 bar and 4000 kelvin. Methane and liquid oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J/kg-k. The nozzle has an exit to throat area ratio of A₂ / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (a) Mass flow rate m for choked flow (b) Critical Mach numbers (c) Critical pressures
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