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An ideal turboprop is used to propel an aircraft at 1524 m. The craft flies with a Mach number of 0.4. The compressor pressure ratio is 4.8, and the airflow through the core is 10.88 kg/s. The burner exit total temperature is 1222 K, and the exit Mach number is 0.7. The heating value of the fuel is 41402.8 kJ/kg. Find the developed thrust, dimensionless hrust and TSEC.

An ideal turboprop is used to propel an aircraft at 1524 m. The craft flies with a Mach number of 0.4. The compressor pressure ratio is 4.8, and the airflow through the core is 10.88 kg/s. The burner exit total temperature is 1222 K, and the exit Mach number is 0.7. The heating value of the fuel is 41402.8 kJ/kg. Find the developed thrust, dimensionless hrust and TSEC.

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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An ideal turboprop is used to propel an aircraft at 1524 m. The craft flies with a Mach number of 0.4. The compressor pressure ratio is 4.8, and the airflow through the core is 10.88 kg/s. The burner exit total temperature is 1222 K, and the exit Mach number is 0.7. The heating value of the fuel is 41402.8 kJ/kg. Find the developed thrust, dimensionless thrust, and TSFC.
Transcribed Image Text:An ideal turboprop is used to propel an aircraft at 1524 m. The craft flies with a Mach number of 0.4. The compressor pressure ratio is 4.8, and the airflow through the core is 10.88 kg/s. The burner exit total temperature is 1222 K, and the exit Mach number is 0.7. The heating value of the fuel is 41402.8 kJ/kg. Find the developed thrust, dimensionless thrust, and TSFC.
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