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Approximate Solutions of the Hypersonic Laminar Boundary Layer Equations with Heat Transfer and Arbitrary Pressure Gradient and Their Applications
https://jaxa.repo.nii.ac.jp/records/34608
https://jaxa.repo.nii.ac.jp/records/346086e0acc0d-0674-4b46-911d-30143705f4f6
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
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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 | Approximate Solutions of the Hypersonic Laminar Boundary Layer Equations with Heat Transfer and Arbitrary Pressure Gradient and Their Applications | |||||||
| 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 |
NARUSE, Humio
× NARUSE, Humio
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| 出版者 | ||||||||
| 出版者 | 東京大学航空研究所 | |||||||
| 出版者(英) | ||||||||
| 出版者 | Aeronautical Research Institute, University of Tokyo | |||||||
| 書誌情報 |
東京大學航空研究所報告 en : Report/Aeronautical Research Institute, University of Tokyo 巻 27, 号 1, p. 1-30, 発行日 1961-02 |
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| 抄録(英) | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | A useful integral method is presented, by which approximate formulae can be derived for the thickness and the displacement thickness of the boundary layer and also for the skin-friction and the heat-transfer coefficients related to it, assuming constant specific heats, Prandtl number of unity and the law of linear variation of viscosity with temperature. Approximate formulae are derived for the case of an arbitrary pressure distribution, a constant temperature on the wall and a large Mach number in the main flow. Comparison with other authors' formulae, obtained for the case where similar solutions exist, shows a sufficient accuracy of our formulae. | |||||||
| ISSN | ||||||||
| 収録物識別子タイプ | ISSN | |||||||
| 収録物識別子 | 0376-1061 | |||||||
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| 収録物識別子タイプ | NCID | |||||||
| 収録物識別子 | AA00514444 | |||||||
| 資料番号 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 資料番号: SA2404857000 | |||||||