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Aerodynamic performance of axial-flow fan stage operated at nine inlet guide vane angles. [to be used on vertical lift aircraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reid, L. Moore, R. D. |
| Copyright Year | 1979 |
| Description | The overall performance of a fan stage with nine inlet guide vane angle settings is presented. These data were obtained over the stable flow range at speeds from 60 to 120 percent of design for vane setting angles from -25 to 42.5 degrees. At design speed and design inlet guide vane angle, the stage has a peak efficiency of 0.892 at a pressure ratio of 1.322 and a flow of 25.31 kg/s. The stall margin based on peak efficiency and stall was 20 percent. Based on an operating line passing through the peak efficiency point at the design setting angle, the useful operating range of the stage at design speed is limited by stall at the positive setting angles and by choke at the negative angles. At design the calculated static thrust along the operating line varied from 68 to 114 percent of that obtained at design setting angle. |
| File Size | 1873961 |
| Page Count | 43 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790023043 |
| Archival Resource Key | ark:/13960/t4tj39t5w |
| Language | English |
| Publisher Date | 1979-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Performance Tests Engine Inlets Engine Tests Guide Vanes Vertical Takeoff Aircraft Thrust Measurement Tables Data Air Flow Axial Flow Turbines Jet Thrust Rotor Blades Turbomachinery Lift Fans Stator Blades 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 |
