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Performance of inlet stage of transonic compressor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lewis Jr., G. W. Steinke, R. J. Urasek, D. C. |
| Copyright Year | 1976 |
| Description | The overall and blade-element performances are presented over the stable flow operating range of the stage at the design tip speed of 426 m/sec. Stage peak efficiency of 0.83 was obtained at a weight flow of 28.8 kg/sec and a pressure ratio of 1.52. The stall margin for the stage was 8 percent based on weight flow and pressure ratio at peak efficiency and stall. The rotor appears to be stalling prematurely as evidenced by high rotor tip losses. |
| File Size | 4614839 |
| Page Count | 73 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760009935 |
| Archival Resource Key | ark:/13960/t49p7tq8f |
| Language | English |
| Publisher Date | 1976-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Tables Data Turbocompressors Performance Tests Transonic Flow Compressor Rotors Compressor Blades Performance Prediction Flow Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
