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Performance of the components of the xj34-we-32 turbojet engine over a range of engine and flight conditions
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form. |
| File Size | 27455365 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930087487 |
| Archival Resource Key | ark:/13960/t7jq59w3n |
| Language | English |
| Publisher Date | 1952-06-09 |
| Access Restriction | Open |
| Subject Keyword | Engines, Turbo-jet Compressors-axial Flow Combustion Research-general Turbines-axial Flow 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 |