Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization
The objective of this study is to enhance the methodology for the design of a supersonic wind tunnel, improving the process with advanced computational techniques. The supersonic wind tunnel is intended to operate within a flight envelope of Mach 2.5 to 4 and altitudes between 18 and 20 km; this stu...
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MDPI AG
2025-04-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/12/5/366 |
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| author | Riccardo Nicoletti Francesco Margani Luca Armani Antonella Ingenito Chihiro Fujio Hideaki Ogawa Seoeum Han Bok Jik Lee |
| author_facet | Riccardo Nicoletti Francesco Margani Luca Armani Antonella Ingenito Chihiro Fujio Hideaki Ogawa Seoeum Han Bok Jik Lee |
| author_sort | Riccardo Nicoletti |
| collection | DOAJ |
| description | The objective of this study is to enhance the methodology for the design of a supersonic wind tunnel, improving the process with advanced computational techniques. The supersonic wind tunnel is intended to operate within a flight envelope of Mach 2.5 to 4 and altitudes between 18 and 20 km; this study focuses on the operative condition of Mach 3.5. The research is based on computational fluid dynamics, enabling a deeper understanding of fluid flow phenomena that can deteriorate the operability of the wind tunnel. Additionally, a detailed mesh independence study has been conducted to ensure the reliability and robustness of the computational results. These new analyses allowed for a more comprehensive optimization in the state of the art of tunnel geometry and operational conditions, further enhancing the ability to sustain supersonic flow for extended durations. Particular attention was given to the second throat, which plays a crucial role in the overall performance of the facility, especially during the start-up process. Its design has been refined to improve efficiency by reducing the minimum starting pressure. |
| format | Article |
| id | doaj-art-b4494e8ddf5a4356b9659bfb7e58187c |
| institution | OA Journals |
| issn | 2226-4310 |
| language | English |
| publishDate | 2025-04-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj-art-b4494e8ddf5a4356b9659bfb7e58187c2025-08-20T02:33:39ZengMDPI AGAerospace2226-43102025-04-0112536610.3390/aerospace12050366Numerical Investigation of a Supersonic Wind Tunnel Diffuser OptimizationRiccardo Nicoletti0Francesco Margani1Luca Armani2Antonella Ingenito3Chihiro Fujio4Hideaki Ogawa5Seoeum Han6Bok Jik Lee7Department of Advanced Space Propulsion, Scuola di Ingegneria Aerospaziale, University of Rome La Sapienza, 00185 Roma, ItalyDepartment of Advanced Space Propulsion, Scuola di Ingegneria Aerospaziale, University of Rome La Sapienza, 00185 Roma, ItalyDepartment of Advanced Space Propulsion, Scuola di Ingegneria Aerospaziale, University of Rome La Sapienza, 00185 Roma, ItalyDepartment of Advanced Space Propulsion, Scuola di Ingegneria Aerospaziale, University of Rome La Sapienza, 00185 Roma, ItalyDepartment of Aeronautics and Astronautics, Kyushu University, Fukuoka 819-0395, JapanDepartment of Aeronautics and Astronautics, Kyushu University, Fukuoka 819-0395, JapanDepartment of Aerospace Engineering, Seoul National University, Seoul 08826, Republic of KoreaDepartment of Aerospace Engineering, Seoul National University, Seoul 08826, Republic of KoreaThe objective of this study is to enhance the methodology for the design of a supersonic wind tunnel, improving the process with advanced computational techniques. The supersonic wind tunnel is intended to operate within a flight envelope of Mach 2.5 to 4 and altitudes between 18 and 20 km; this study focuses on the operative condition of Mach 3.5. The research is based on computational fluid dynamics, enabling a deeper understanding of fluid flow phenomena that can deteriorate the operability of the wind tunnel. Additionally, a detailed mesh independence study has been conducted to ensure the reliability and robustness of the computational results. These new analyses allowed for a more comprehensive optimization in the state of the art of tunnel geometry and operational conditions, further enhancing the ability to sustain supersonic flow for extended durations. Particular attention was given to the second throat, which plays a crucial role in the overall performance of the facility, especially during the start-up process. Its design has been refined to improve efficiency by reducing the minimum starting pressure.https://www.mdpi.com/2226-4310/12/5/366supersonic wind tunnelblowdown wind tunnelCFDsecond throat optimizationnozzle designhypersonic |
| spellingShingle | Riccardo Nicoletti Francesco Margani Luca Armani Antonella Ingenito Chihiro Fujio Hideaki Ogawa Seoeum Han Bok Jik Lee Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization Aerospace supersonic wind tunnel blowdown wind tunnel CFD second throat optimization nozzle design hypersonic |
| title | Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization |
| title_full | Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization |
| title_fullStr | Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization |
| title_full_unstemmed | Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization |
| title_short | Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization |
| title_sort | numerical investigation of a supersonic wind tunnel diffuser optimization |
| topic | supersonic wind tunnel blowdown wind tunnel CFD second throat optimization nozzle design hypersonic |
| url | https://www.mdpi.com/2226-4310/12/5/366 |
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