A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference
May 1979
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| Format: | Technical Report |
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Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979]
2016
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| Online Access: | http://hdl.handle.net/1721.1/104422 |
| _version_ | 1811084375306010624 |
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| author | Haymann-Haber, Guido |
| author2 | Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory |
| author_facet | Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory Haymann-Haber, Guido |
| author_sort | Haymann-Haber, Guido |
| collection | MIT |
| description | May 1979 |
| first_indexed | 2024-09-23T12:49:44Z |
| format | Technical Report |
| id | mit-1721.1/104422 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T12:49:44Z |
| publishDate | 2016 |
| publisher | Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979] |
| record_format | dspace |
| spelling | mit-1721.1/1044222019-04-10T14:24:36Z A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference Haymann-Haber, Guido Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory TJ778.M41 G24 no.145 Compressors -- Aerodynamics Aerodynamics, Transonic May 1979 Originally presented as the author's thesis, M.S., in the M.I.T. Dept. of Aeronautics and Astronautics, 1979 Includes bibliographical references (leaf 82) A computational study of the flow in a Transonic Axial Compressor has been performed. This compressor has a tip Mach number of 1.2 and an inlet hub to tip ratio of 0.5. The numerical procedure used is a fully three-dimensional, inviscid, finite difference algorithm. MacCormack's two-step, explicit second order accurate scheme was used. A total of 30,600 mesh points were used. The results were compared to space and time resolved exit flow measurements, and to quantitative density visualization pictures. Among the most significant features resolved by the computation, was an unusual shock structure, which had earlier been observed in the experiments. The general agreement of the computation with The experiment is good, except in regions dominated by viscous flow. Many of the effects of viscosity can be anticipated from the inviscid flow field. Supported by the NASA Lewis Research Center under Grant NGL 22-009-383 2016-09-27T19:59:07Z 2016-09-27T19:59:07Z 1979 Technical Report http://hdl.handle.net/1721.1/104422 06550488 GT & PDL report ; no. 145 82 leaves application/pdf Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979] |
| spellingShingle | TJ778.M41 G24 no.145 Compressors -- Aerodynamics Aerodynamics, Transonic Haymann-Haber, Guido A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title | A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title_full | A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title_fullStr | A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title_full_unstemmed | A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title_short | A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference |
| title_sort | computational study of the flow in a transonic axial compressor using an inviscid three dimensional finite difference |
| topic | TJ778.M41 G24 no.145 Compressors -- Aerodynamics Aerodynamics, Transonic |
| url | http://hdl.handle.net/1721.1/104422 |
| work_keys_str_mv | AT haymannhaberguido acomputationalstudyoftheflowinatransonicaxialcompressorusinganinviscidthreedimensionalfinitedifference AT haymannhaberguido computationalstudyoftheflowinatransonicaxialcompressorusinganinviscidthreedimensionalfinitedifference |