A decomposition formula for the wall heat flux of a compressible boundary layer
Abstract Understanding the generation mechanism of the heat flux is essential for the design of hypersonic vehicles. We proposed a novel formula to decompose the heat flux coefficient into the contributions of different terms by integrating the conservative equation of the total energy. The reliabil...
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| Автори: | , , , , , |
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| Формат: | Artigo |
| Мова: | Inglês |
| Опубліковано: |
SpringerOpen
2021-11-01
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| Серія: | Advances in Aerodynamics |
| Предмети: | |
| Онлайн доступ: | https://doi.org/10.1186/s42774-021-00081-y |
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