Supersonic leeside flow topology on delta wings revisited
Brodetsky, M. D. ; Kharitonov, A. M. ; Krause, E. ; Pavlov, A. A. ; Nikiforov, S. B. ; Shevchenko, A. M.
Springer
Published 2000
Springer
Published 2000
| ISSN: |
1432-1114
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|---|---|
| Source: |
Springer Online Journal Archives 1860-2000
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| Topics: |
Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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| Notes: |
Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported.
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| Type of Medium: |
Electronic Resource
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| URL: |
| _version_ | 1798295601012539392 |
|---|---|
| autor | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| autorsonst | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| book_url | http://dx.doi.org/10.1007/s003480000127 |
| datenlieferant | nat_lic_papers |
| hauptsatz | hsatz_simple |
| identnr | NLM203338782 |
| issn | 1432-1114 |
| journal_name | Experiments in fluids |
| materialart | 1 |
| notes | Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. |
| package_name | Springer |
| publikationsjahr_anzeige | 2000 |
| publikationsjahr_facette | 2000 |
| publikationsjahr_intervall | 7999:2000-2004 |
| publikationsjahr_sort | 2000 |
| publisher | Springer |
| reference | 29 (2000), S. 592-604 |
| search_space | articles |
| shingle_author_1 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| shingle_author_2 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| shingle_author_3 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| shingle_author_4 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. |
| shingle_catch_all_1 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. Supersonic leeside flow topology on delta wings revisited Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. 1432-1114 14321114 Springer |
| shingle_catch_all_2 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. Supersonic leeside flow topology on delta wings revisited Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. 1432-1114 14321114 Springer |
| shingle_catch_all_3 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. Supersonic leeside flow topology on delta wings revisited Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. 1432-1114 14321114 Springer |
| shingle_catch_all_4 | Brodetsky, M. D. Kharitonov, A. M. Krause, E. Pavlov, A. A. Nikiforov, S. B. Shevchenko, A. M. Supersonic leeside flow topology on delta wings revisited Abstract The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of χ=68°, 73°, and 78° and parabolic profiles in the 0.6 × 0.6 m2 test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M=2 to 4, unit Reynolds numbers from Re l=26 × 106 to 56 × 106 m−1, and angles of attack from α=0° to 22°. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. 1432-1114 14321114 Springer |
| shingle_title_1 | Supersonic leeside flow topology on delta wings revisited |
| shingle_title_2 | Supersonic leeside flow topology on delta wings revisited |
| shingle_title_3 | Supersonic leeside flow topology on delta wings revisited |
| shingle_title_4 | Supersonic leeside flow topology on delta wings revisited |
| sigel_instance_filter | dkfz geomar wilbert ipn albert fhp |
| source_archive | Springer Online Journal Archives 1860-2000 |
| timestamp | 2024-05-06T09:38:47.611Z |
| titel | Supersonic leeside flow topology on delta wings revisited |
| titel_suche | Supersonic leeside flow topology on delta wings revisited |
| topic | ZL |
| uid | nat_lic_papers_NLM203338782 |