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Performance Charts for a Turbojet SystemConvenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion-chamber-outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge-nozzle coefficient, losses in total pressure in the inlet to the jet-propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion-chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion-chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials.
Document ID
19930093534
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
Authors
Karp, Irving M.
Date Acquired
August 16, 2013
Publication Date
June 1, 1947
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-ARR-E6E14
NACA-WR-E-241
Accession Number
93R22824
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
CHARTS-PERFORMANCE-ENGINES, TURBOJET
ENGINES, TURBOJET-PERFORMANCE

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