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Performance of axial-flow supersonic compressor on xj-55-ff-1 turbojet engine. i - preliminary performance of compressor. 1; preliminary performance of compressor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1949 |
| Description | An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ-55-FF-1 turbo Jet engine. The test unit consisted of a row of inlet guide vanes and a supersonic rotor; the stator vanes after the rotor were omitted. The maximum pressure ratio produced in the single stage was 2.28 at an equivalent tip speed or 1814 feet per second with an adiabatic efficiency of approximately 0.61, equivalent weight flow of 13.4 pounds per second. The maximum efficiency of 0.79 was obtained at an equivalent tip speed of 801 feet per second. |
| File Size | 2398663 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20090026509 |
| Archival Resource Key | ark:/13960/t6158xg7b |
| Language | English |
| Publisher Date | 1949-01-30 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power 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 |
