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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
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 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
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 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
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