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altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine vi : combustion-chamber performanceAn analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust axial-flow turbojet engine is presented. The data were obtained from investigations of the complete engine over a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.00 to 1.86. The combustion-chamber pressure losses, the effect of the losses on cycle efficiency, and the combustion efficiency are discussed.
Document ID
19930093755
Document Type
Other
Authors
Pinkel, I Irving
Shames, Harold
Date Acquired
August 16, 2013
Publication Date
August 4, 1948
Report/Patent Number
NACA-RM-E8F09e
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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