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Investigation of 10-stage axial-flow x24c-2 compressor. 1; performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 r
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1947 |
| Description | The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived. |
| File Size | 2126375 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030064117 |
| Archival Resource Key | ark:/13960/t9p31702r |
| Language | English |
| Publisher Date | 1947-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power 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 |
