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Altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine. 3; performance characteristics with the high-flow compressor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors. |
| File Size | 2012003 |
| Page Count | 71 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030064118 |
| Archival Resource Key | ark:/13960/t1tf44m26 |
| Language | English |
| Publisher Date | 1948-08-05 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power 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 |