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Performance of tandem-bladed transonic compressor rotor with tip speed of 1375 feet per second
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Janetzke, D. C. Urasek, D. C. |
| Copyright Year | 1972 |
| Description | The design and experimental performance of a 20-inch diameter tandem-bladed axial-flow transonic compressor rotor is presented. Radial surveys were made of the flow conditions. At design speed the peak efficiency was 0.88 and occurred at an equivalent weight flow of 63 pounds per second. At peak efficiency the total pressure and total temperature ratios were 1.77 and 1.20, respectively. The stall margin at design speed was 10 percent based on weight flows and total pressure ratios at peak efficiency and near stall. |
| File Size | 6801129 |
| Page Count | 89 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720011123 |
| Archival Resource Key | ark:/13960/t48q0s981 |
| Language | English |
| Publisher Date | 1972-03-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Boundary Layer Separation Compressor Rotors Transonic Flow Compressor Blades Transonic Compressors Air Breathing Engines Separated Flow Axial Flow 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 |
