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Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. part 2: data and performance for stage a
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Brent, J. A. |
| Copyright Year | 1972 |
| Description | Stage A, comprised of a conventional rotor and stator, was designed and tested to establish a performance baseline for comparison with the results of subsequent tests planned for two tandem-blade stages. The rotor had an inlet hub/tip ratio of 0.8 and a design tip velocity of 757 ft/sec. At design equivalent rotor speed, rotor A achieved a maximum adiabatic efficiency of 85.1 percent at a pressure ratio of 1.29. The stage maximum adiabatic efficiency was 78.6 percent at a pressure ratio of 1.27. |
| File Size | 14736821 |
| Page Count | 112 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720019040 |
| Archival Resource Key | ark:/13960/t9x10vq0r |
| Language | English |
| Publisher Date | 1972-07-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Stators Airfoils Adiabatic Conditions Compressor Rotors Rotor Blades Turbomachinery 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 |
