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Aerodynamic Study of Stagnation Ablation
https://jaxa.repo.nii.ac.jp/records/34394
https://jaxa.repo.nii.ac.jp/records/343940022d1f5-5703-423c-aeac-e6e7341175b2
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2400555.pdf (2.0 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||||
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| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | Aerodynamic Study of Stagnation Ablation | |||||||||
| 言語 | en | |||||||||
| 言語 | ||||||||||
| 言語 | eng | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||||
| 資源タイプ | departmental bulletin paper | |||||||||
| 著者 |
KARASHIMA, Keiichi
× KARASHIMA, Keiichi
× KUBOTA, Hirotoshi
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| 出版者 | ||||||||||
| 出版者 | 東京大学宇宙航空研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Institute of Space and Aeronautical Science,University of Tokyo | |||||||||
| 書誌情報 |
en : ISAS report/Institute of Space and Aeronautical Science,University of Tokyo 巻 32, 号 6, p. 87-119, 発行日 1967-06 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Present paper gives detailed results of a theoretical approach to stagnation ablation associated with hypersonic reentry of blunt-nosed bodies of revolution. Fundamental equations are derived, under an assumption of sublimating ablation. for a non-reacting laminar boundary layer flow of binary gas mixture, in which transport properties are taken exactly into consideration by use of the atomic kinetic theory of gases. It is shown that all physical properties concerning the ablating field can be uniquely determined under the given boundary conditions by matching of an aerodynamic solution with a static one obtained from chemical kinetics. Detailed examination reveals that error in estimation of Chapman-Rubesin number and Schmidt number across the boundary layer is most sensitive to the aerodynamic solutions, thus indicating that viscosity and diffusivity of gas mixture play a main role in controlling the flow characteristics of the ablating field. Numerical calculation carried out for teflon ablator shows that the ablation rate increases with increase of stagnation temperature in free stream, while wall temperature does not rise so much, indicating that teflon is a fairly good ablator as a shield of aerodynamic heating for comparatively low enthalpy flow. In order to confirm validity of the present approach, theoretical results are compared with experimental data for teflon. Agreement between theory and experiment is fairly good in the range of stagnation temperature from 800℃ to 1200℃. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0372-1418 | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA00675986 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA2400555000 | |||||||||
