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Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle
| Title: | Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle |
| Authors: | Yu, Minghao Browse this author | | Qiu, Zeyang Browse this author | | Zhong, Bowen Browse this author | | Takahashi, Yusuke Browse this author →KAKEN DB |
| Issue Date: | 8-Dec-2022 |
| Publisher: | AIP Publishing |
| Journal Title: | Physics of fluids |
| Volume: | 34 |
| Issue: | 12 |
| Start Page: | 126103 |
| Publisher DOI: | 10.1063/5.0131460 |
| Abstract: | A multi-physics thermochemical non-equilibrium model is established to study the flow characteristics of the plasma sheath around an atmospheric reentry demonstrator. This model includes the tight coupling of Navier-Stokes equations, 54 chemical reactions of air, and a four-temperature model. The processes of dissociation, ionization, and the internal energy exchanges of air components were successfully simulated during aerodynamic heating of the reentry vehicle. The distributions of plasma sheath temperature, the molar fraction of air species, stagnation pressure, surface pressure, and electron number density around the reentry vehicle were obtained at different flight altitudes. Additionally, to validate the numerical model developed in this study, the flow characteristics of the Radio Attenuation Measurement-C-II (RAM-C-II) vehicle are also simulated and then compared with corresponding experimental data. They show good consistency in general. It is found that when the vehicle is at a high flight altitude, there is a strong thermochemical non-equilibrium phenomenon around the vehicle. However, the plasma sheath tends to be in local thermal equilibrium at a low flight altitude. The distance from the shock layer to the stagnation point decreases with a decrease in reentry altitude from 90 to 65 km but increases with a decrease from 65 to 40 km. The electron number density in the shock layer is maximum. The distribution of the electron number density in the wake region differs significantly at different flight altitudes. |
| Rights: | This article may be downloaded for personal use only. Any other use requires prior permission of the author and AIP Publishing. This article appeared in Minghao Yu, Zeyang Qiu, Bowen Zhong, and Yusuke Takahashi, "Numerical simulation of thermochemical non-equilibrium flow-field characteristics around a hypersonic atmospheric reentry vehicle", Physics of Fluids 34, 126103 (2022) and may be found at https://doi.org/10.1063/5.0131460. |
| Type: | article |
| URI: | http://hdl.handle.net/2115/90867 |
| Appears in Collections: | 工学院・工学研究院 (Graduate School of Engineering / Faculty of Engineering) > 雑誌発表論文等 (Peer-reviewed Journal Articles, etc)
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Submitter: 高橋 裕介
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