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Altitude wind tunnel investigation of the performance of compressor, combustor, and turbine components of prototype j47d (rx1-1) turbojet engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1951 |
| Description | As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be controlled separately. Two combustor configurations were investigated. |
| File Size | 20657582 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086850 |
| Archival Resource Key | ark:/13960/t4xh3z14j |
| Language | English |
| Publisher Date | 1951-12-21 |
| Access Restriction | Open |
| Subject Keyword | Engines, Turbo-jet Compressors - Axial Flow Combustion -turbine Engines 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 |
