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Analytical investigation of supersonic turbomachinery blading. 2 - analysis of impulse turbine-blade sections
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1968 |
| Description | Surface Mach numbers, inlet flow angle, and specific heat ratio effects on geometric features of supersonic impulse turbine blade sections in Mach range 1.5 to 5.0 |
| File Size | 1069230 |
| Page Count | 25 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19680010807 |
| Archival Resource Key | ark:/13960/t6n05wf38 |
| Language | English |
| Publisher Date | 1968-04-01 |
| Access Restriction | Open |
| Subject Keyword | Auxiliary Systems Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |