Numerical and Experimental Validation of a Supersonic Mixing Layer Facility
The design of a supersonic-supersonic mixing layer facility was motivated by the need for a benchmark experimental platform to study the physical phenomena underlying supersonic mixing layers. The facility is an intermittent blowdown wind tunnel characterized by a two-stream design separated by a sp...
| Principais autores: | , , , , |
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| Formato: | Artigo |
| Idioma: | English |
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MDPI AG
2022-05-01
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| coleção: | Applied Sciences |
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| Acesso em linha: | https://www.mdpi.com/2076-3417/12/11/5489 |
| _version_ | 1827665641261236224 |
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| author | Yudong Li Li Chen Hongxun Li Yungang Wu Shuang Chen |
| author_facet | Yudong Li Li Chen Hongxun Li Yungang Wu Shuang Chen |
| author_sort | Yudong Li |
| collection | DOAJ |
| description | The design of a supersonic-supersonic mixing layer facility was motivated by the need for a benchmark experimental platform to study the physical phenomena underlying supersonic mixing layers. The facility is an intermittent blowdown wind tunnel characterized by a two-stream design separated by a splitter plate in the middle of the nozzle. The splitter plate ends exactly at the start of the mixing layer test section. The Mach number of the primary stream is M<sub>1</sub> = 3 for all nozzles and the secondary streams are M<sub>2</sub> = 2, 2.5, and 2.9 to generate different convective Mach numbers of Mc = 0.25, 0.10, and 0.01, respectively. The facility was calibrated by pressure measurements to verify the Mach number and the pressure distribution in the streamwise direction. Large-eddy simulation (LES) was performed to illustrate a full view of the turbulent compressible mixing layer flow field and to compare this against the experimental data. Optical diagnosis measurements, i.e., femtosecond laser-induced electronic excitation tagging velocimetry (FLEET) for velocity measurement and focused laser differential interferometer (FLDI) for the density fluctuation, were also performed on the facility. |
| first_indexed | 2024-03-10T01:30:58Z |
| format | Article |
| id | doaj.art-bfffc41e77f9492f9a75dbd9e8594b53 |
| institution | Directory Open Access Journal |
| issn | 2076-3417 |
| language | English |
| last_indexed | 2024-03-10T01:30:58Z |
| publishDate | 2022-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Applied Sciences |
| spelling | doaj.art-bfffc41e77f9492f9a75dbd9e8594b532023-11-23T13:42:35ZengMDPI AGApplied Sciences2076-34172022-05-011211548910.3390/app12115489Numerical and Experimental Validation of a Supersonic Mixing Layer FacilityYudong Li0Li Chen1Hongxun Li2Yungang Wu3Shuang Chen4Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaFacility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaFacility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaFacility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaFacility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, ChinaThe design of a supersonic-supersonic mixing layer facility was motivated by the need for a benchmark experimental platform to study the physical phenomena underlying supersonic mixing layers. The facility is an intermittent blowdown wind tunnel characterized by a two-stream design separated by a splitter plate in the middle of the nozzle. The splitter plate ends exactly at the start of the mixing layer test section. The Mach number of the primary stream is M<sub>1</sub> = 3 for all nozzles and the secondary streams are M<sub>2</sub> = 2, 2.5, and 2.9 to generate different convective Mach numbers of Mc = 0.25, 0.10, and 0.01, respectively. The facility was calibrated by pressure measurements to verify the Mach number and the pressure distribution in the streamwise direction. Large-eddy simulation (LES) was performed to illustrate a full view of the turbulent compressible mixing layer flow field and to compare this against the experimental data. Optical diagnosis measurements, i.e., femtosecond laser-induced electronic excitation tagging velocimetry (FLEET) for velocity measurement and focused laser differential interferometer (FLDI) for the density fluctuation, were also performed on the facility.https://www.mdpi.com/2076-3417/12/11/5489supersonic mixing layerwind tunnelLES simulationoptical diagnosis |
| spellingShingle | Yudong Li Li Chen Hongxun Li Yungang Wu Shuang Chen Numerical and Experimental Validation of a Supersonic Mixing Layer Facility Applied Sciences supersonic mixing layer wind tunnel LES simulation optical diagnosis |
| title | Numerical and Experimental Validation of a Supersonic Mixing Layer Facility |
| title_full | Numerical and Experimental Validation of a Supersonic Mixing Layer Facility |
| title_fullStr | Numerical and Experimental Validation of a Supersonic Mixing Layer Facility |
| title_full_unstemmed | Numerical and Experimental Validation of a Supersonic Mixing Layer Facility |
| title_short | Numerical and Experimental Validation of a Supersonic Mixing Layer Facility |
| title_sort | numerical and experimental validation of a supersonic mixing layer facility |
| topic | supersonic mixing layer wind tunnel LES simulation optical diagnosis |
| url | https://www.mdpi.com/2076-3417/12/11/5489 |
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