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 Ae / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (d) For launch at sea level Pb = 101.325 kilopascals, is the nozzle over, under, or perfectly expanded? (e) Is the nozzle flow choked? (f) Exit temperature

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 Ae / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (d) For launch at sea level Pb = 101.325 kilopascals, is the nozzle over, under, or perfectly expanded? (e) Is the nozzle flow choked? (f) Exit temperature

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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