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Effect of compressor-outlet bleedoff on turbojet-engine performance
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1950 |
| Description | An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed. |
| File Size | 15127828 |
| Page Count | 29 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086139 |
| Archival Resource Key | ark:/13960/t58d47v4b |
| Language | English |
| Publisher Date | 1950-08-07 |
| Access Restriction | Open |
| Subject Keyword | Turbines, Gas - Bleed-off Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |