| dc.contributor.author | McCune, James E. (James Elliot) | en_US |
| dc.contributor.author | Dharwadkar, Shashikant Prabhakar | en_US |
| dc.contributor.other | Massachusetts Institute of Technology. Gas Turbine Laboratory | en_US |
| dc.date.accessioned | 2016-10-06T21:22:01Z | |
| dc.date.available | 2016-10-06T21:22:01Z | |
| dc.date.issued | 1972 | en_US |
| dc.identifier.uri | http://hdl.handle.net/1721.1/104693 | |
| dc.description | July 1972 | en_US |
| dc.description | Includes bibliographical references (leaf 25) | en_US |
| dc.description.abstract | The three-dimensional compressible vortex theory of an axial compressor rotor or ducted fan is extended by relating blade loading to blade geometry in the lifting-line approximation. The resulting integral equation, which is valid up to high subsonic Mach numbers, is solved for both design and off-design problems. It is shown that three-dimensional effects must be taken into account, for rotors with non-uniform spanwise loading, in order to obtain accurate predictions of flow angles and other performance parameters. | en_US |
| dc.description.sponsorship | This Research carried out in the Gas Turbine Laboratory, M.I.T., supported by NASA Lewis Research Center, under Grant No. NGL 22-009-383 | en_US |
| dc.format.extent | v, 36 leaves | en_US |
| dc.publisher | Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1972] | en_US |
| dc.relation.ispartofseries | GTL report #110 | en_US |
| dc.subject.lcc | TJ778.M41 G24 no.110 | en_US |
| dc.subject.lcsh | Compressors -- Blades | en_US |
| dc.subject.lcsh | Lift (Aerodynamics) | en_US |
| dc.title | Lifting-line theory for subsonic axial compressor rotors | en_US |
| dc.type | Technical Report | en_US |
| dc.identifier.oclc | 09677041 | en_US |
