Parameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle Geometry
Parameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle Geometry
Refrigeration and Air Conditioning Technology (MindTap Course List)
8th Edition
ISBN:9781305578296
Author:John Tomczyk, Eugene Silberstein, Bill Whitman, Bill Johnson
Publisher:John Tomczyk, Eugene Silberstein, Bill Whitman, Bill Johnson
Chapter46: Room Air Conditioners
Section: Chapter Questions
Problem 15RQ
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