Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle
The substantial aerodynamic drag and severe aerothermal loads, which are closely related to boundary layer transition, challenge the design of hypersonic vehicles and could be relieved by active methods aimed at drag and heat flux reduction, such as aerodisk. However, the research of aerodisk effect...
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-11-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/9/12/742 |
| _version_ | 1827642373502402560 |
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| author | Yatian Zhao Zhiyuan Shao Hongkang Liu |
| author_facet | Yatian Zhao Zhiyuan Shao Hongkang Liu |
| author_sort | Yatian Zhao |
| collection | DOAJ |
| description | The substantial aerodynamic drag and severe aerothermal loads, which are closely related to boundary layer transition, challenge the design of hypersonic vehicles and could be relieved by active methods aimed at drag and heat flux reduction, such as aerodisk. However, the research of aerodisk effects on transitional flows is still not abundant. Based on the improved <i>k-ω-γ</i> transition model, this study investigates the influence of the aerodisk with various lengths on hypersonic boundary layer transition and surface heat flux distribution over HIFiRE-5 configuration under various angles of attack. Certain meaningful analysis and results are obtained: (i) The existence of aerodisk is found to directly trigger separation-induced transition, moving the transition onset near the centerline upstream and widening the transition region; (ii) The maximum wall heat flux could be effectively reduced by aerodisk up to 52.1% and the maximum surface pressure can even be reduced up to 80.4%. The transition shapes are identical, while the variety of growth rates of intermittency are non-monotonous with the increase in aerodisk length. The dilation of region with high heat flux boundary layer is regarded as an inevitable compromise to reducing maximum heat flux and maximum surface pressure. (iii) With the angle of attack rising, first, the transition is postponed and subsequently advanced on the windward surface, which is in contrast to the continuously extending transition region on the leeward surface. This numerical study aims to explore the effects of aerodisk on hypersonic boundary layer transition, enrich the study of hypersonic flow field characteristics and active thermal protection system considering realistic boundary layer transition, and provide references for the excogitation and utilization of hypersonic vehicle aerodisk. |
| first_indexed | 2024-03-09T17:27:31Z |
| format | Article |
| id | doaj.art-fc0054e30c94400ebfcba6c05a872ee4 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T17:27:31Z |
| publishDate | 2022-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-fc0054e30c94400ebfcba6c05a872ee42023-11-24T12:37:14ZengMDPI AGAerospace2226-43102022-11-0191274210.3390/aerospace9120742Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 VehicleYatian Zhao0Zhiyuan Shao1Hongkang Liu2Key Laboratory of Traffic Safety on Track of Ministry of Education, School of Traffic & Transportation Engineering, Central South University, Changsha 410075, ChinaResearch Institute of Aerospace Technology, Central South University, Changsha 410083, ChinaKey Laboratory of Traffic Safety on Track of Ministry of Education, School of Traffic & Transportation Engineering, Central South University, Changsha 410075, ChinaThe substantial aerodynamic drag and severe aerothermal loads, which are closely related to boundary layer transition, challenge the design of hypersonic vehicles and could be relieved by active methods aimed at drag and heat flux reduction, such as aerodisk. However, the research of aerodisk effects on transitional flows is still not abundant. Based on the improved <i>k-ω-γ</i> transition model, this study investigates the influence of the aerodisk with various lengths on hypersonic boundary layer transition and surface heat flux distribution over HIFiRE-5 configuration under various angles of attack. Certain meaningful analysis and results are obtained: (i) The existence of aerodisk is found to directly trigger separation-induced transition, moving the transition onset near the centerline upstream and widening the transition region; (ii) The maximum wall heat flux could be effectively reduced by aerodisk up to 52.1% and the maximum surface pressure can even be reduced up to 80.4%. The transition shapes are identical, while the variety of growth rates of intermittency are non-monotonous with the increase in aerodisk length. The dilation of region with high heat flux boundary layer is regarded as an inevitable compromise to reducing maximum heat flux and maximum surface pressure. (iii) With the angle of attack rising, first, the transition is postponed and subsequently advanced on the windward surface, which is in contrast to the continuously extending transition region on the leeward surface. This numerical study aims to explore the effects of aerodisk on hypersonic boundary layer transition, enrich the study of hypersonic flow field characteristics and active thermal protection system considering realistic boundary layer transition, and provide references for the excogitation and utilization of hypersonic vehicle aerodisk.https://www.mdpi.com/2226-4310/9/12/742boundary layer transitionhypersonicHIFiRE-5heat transferaerodisk |
| spellingShingle | Yatian Zhao Zhiyuan Shao Hongkang Liu Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle Aerospace boundary layer transition hypersonic HIFiRE-5 heat transfer aerodisk |
| title | Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle |
| title_full | Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle |
| title_fullStr | Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle |
| title_full_unstemmed | Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle |
| title_short | Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle |
| title_sort | aerodisk effect on hypersonic boundary layer transition and heat transfer of hifire 5 vehicle |
| topic | boundary layer transition hypersonic HIFiRE-5 heat transfer aerodisk |
| url | https://www.mdpi.com/2226-4310/9/12/742 |
| work_keys_str_mv | AT yatianzhao aerodiskeffectonhypersonicboundarylayertransitionandheattransferofhifire5vehicle AT zhiyuanshao aerodiskeffectonhypersonicboundarylayertransitionandheattransferofhifire5vehicle AT hongkangliu aerodiskeffectonhypersonicboundarylayertransitionandheattransferofhifire5vehicle |