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Comparison of performance and component frontal areas of hypothetical two-spool and one-spool turbojet engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1956 |
| Description | For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning. |
| File Size | 26842354 |
| Page Count | 58 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088938 |
| Archival Resource Key | ark:/13960/t02z5zd3c |
| Language | English |
| Publisher Date | 1956-01-17 |
| Access Restriction | Open |
| Subject Keyword | Compressor Flow Theory AND Experiment Turbines - Axial-flow Turbines - Matching Compressors - Matching Engines, Turbojet Compressors - Axial-flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
