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Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. 4 - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second
| Content Provider | University of North Texas |
|---|---|
| Author | Graham, Robert C. Hartmann, Melvin J. |
| Organization | Lewis Flight Propulsion Laboratory |
| Description | "An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. An analysis of the performance of the rotor was made based on detailed flow measurements behind the rotor. The compressor apparently did not obtain the design normal-shock configuration in this investigation. A large redistribution of mass occurred toward the root of the rotor over the entire speed range; this condition was so acute at design speed that the tip sections were completely inoperative" (p. 1). |
| File Format | |
| Archival Resource Key | ark:/67531/metadc65233 |
| Language | English |
| Publisher Date | 2018-06-06 |
| Access Restriction | Open |
| Subject Keyword | aircraft performance axial-flow supersonic compressors |
| Content Type | Text |
| Resource Type | Report |
