Students did an experiment on Swansea University jet engine. They measured ambient temperature 16 deg C and ambient pressure 1.02 bar, engine RPM 64,664, thrust 17.5781 N, air flow 42.0557 l/s, fuel flow 8.6914 l/h, gauge combustion pressure 0.2942 bar. The temperature values (deg C) at compressor exit, turbine inlet and exhaust were recorded as 39.84, 869.53, 585.93. Assume density of fuel as 0.8 kg/L. The heating value of fuel is 42580 kJ/kg. The idea gas constant R is 0.287 kJ/kg K, the Cp value for air is 1.005 kJ/kg K and the value of specific heat ratio k is 1.4 Estimate the thrust specific fuel consumption value under ideal conditions (g/N-s) Enter your answer to four decimal places in the box below. answer ASAP would be appreciated
Students did an experiment on Swansea University jet engine. They measured ambient temperature 16 deg C and ambient pressure 1.02 bar, engine RPM 64,664, thrust 17.5781 N, air flow 42.0557 l/s, fuel flow 8.6914 l/h, gauge combustion pressure 0.2942 bar. The temperature values (deg C) at compressor exit, turbine inlet and exhaust were recorded as 39.84, 869.53, 585.93. Assume density of fuel as 0.8 kg/L. The heating value of fuel is 42580 kJ/kg. The idea gas constant R is 0.287 kJ/kg K, the Cp value for air is 1.005 kJ/kg K and the value of specific heat ratio k is 1.4 Estimate the thrust specific fuel consumption value under ideal conditions (g/N-s) Enter your answer to four decimal places in the box below. answer ASAP would be appreciated
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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Students did an experiment on Swansea University jet engine. They measured ambient temperature 16 deg C and ambient pressure 1.02 bar, engine RPM 64,664, thrust 17.5781 N, air flow 42.0557 l/s, fuel flow 8.6914 l/h, gauge combustion pressure 0.2942 bar. The temperature values (deg C) at compressor exit, turbine inlet and exhaust were recorded as 39.84, 869.53, 585.93. Assume density of fuel as 0.8 kg/L. The heating value of fuel is 42580 kJ/kg. The idea gas constant R is 0.287 kJ/kg K, the Cp value for air is 1.005 kJ/kg K and the value of specific heat ratio k is 1.4
Estimate the thrust specific fuel consumption value under ideal conditions (g/N-s)
Enter your answer to four decimal places in the box below.
answer ASAP would be appreciated
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