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Performance of axial-flow supersonic compressor of xj55-ff-1 turbojet engine. ii - performance of inlet guide vanes as separate component
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1949 |
| Description | The inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked. |
| File Size | 1326365 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20090023712 |
| Archival Resource Key | ark:/13960/t7cs0566q |
| Language | English |
| Publisher Date | 1949-05-03 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
