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Performance of a 1.20 pressure ratio stol fan stage at three rotor blade setting angles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kovich, G. Lewis Jr., G. W. Moore, R. D. |
| Copyright Year | 1973 |
| Description | A model of a short takeoff and landing (STOL) fan stage was testedin a single-stage compressor research facility. Surveys of the airflow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 meters per second and a weight flow of 31.2 kilograms per second, the stage pressure ratio of 1.15 was less than the design value of 1.2. The stage was tested with the rotor blades reset for more flow. Design pressure ratio was achieved and surpassed with the minus 5 deg and minus 7 deg resets, respectively. The stage efficiency was 0.88 for the minus 5 deg reset and 0.85 for the minus 7 deg reset. |
| File Size | 12328060 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730018974 |
| Archival Resource Key | ark:/13960/t57d7nf8p |
| Language | English |
| Publisher Date | 1973-07-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Air Flow Performance Tests Numerical Analysis Turbofans Flow Distribution Wind Tunnel Tests Wind Tunnel Models Short Takeoff Aircraft 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 |
