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Turbine for a low cost turbojet engine. 1: design and cold-air performance
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kofskey, M. G. Roelke, R. J. |
| Copyright Year | 1974 |
| Description | A 24.70-cm(9.72-in.) tip diameter single-stage, axial-flow turbine was designed for a turbojet engine. Cold-air tests were made over a range of speeds from 30 to 105 percent of design equivalent speed and over a range of total-pressure ratios from 1.30 to 2.66. Results are presented in terms of specific work, torque, mass flow, and efficiency. |
| File Size | 3149444 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740018139 |
| Archival Resource Key | ark:/13960/t0wq4r49v |
| Language | English |
| Publisher Date | 1974-06-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Equipment Specifications Air Flow Performance Tests Axial Flow Turbines Propulsion System Performance Cold Flow Tests Turbojet Engines 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 |
