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An Aerodynamic Study of Hypersonic Heat Shielding Problem with Local Mass Injection at Multiple Stations
https://jaxa.repo.nii.ac.jp/records/34439
https://jaxa.repo.nii.ac.jp/records/3443946b3fe8a-c7ea-4265-866d-2d8fecc6f6f0
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2400794.pdf (2.5 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||
|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||
| タイトル | ||||||||
| タイトル | An Aerodynamic Study of Hypersonic Heat Shielding Problem with Local Mass Injection at Multiple Stations | |||||||
| 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 |
KUBOTA, Hirotoshi
× KUBOTA, Hirotoshi
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| 著者所属（英） | ||||||||
| en | ||||||||
| Research engineer in the National Aerospace Laboratory | ||||||||
| 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 36, 号 2, p. 37-76, 発行日 1971-03 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | A study of an axisymmetric laminar boundary layer flow with local coolant mass injection at multiple stations is made by use of an appropriate numerical approach on the basis of the Hartree-Womersley method. The essential feature of the problem consists in discontinuous boundary conditions associated with the local blowing. In order to check the accuracy of the H-W method applied to the partial differential equations of parabolic type with discontinuous boundary conditions, one-dimensional heat conduction equation is solved numerically as a simple example under the boundary conditions involving several modes of discontinuity and the results are compared with analytical ones. It is shown that the H-W method is applicable if an appropriate difference method is chosen for each mode of the discontinuity. Based on these arguments, an appropriate difference method is presented for an isothermal and an adiabatic wall conditions. Estimation of cooling effectiveness due to mass injection parameters such as total mass flow and geometrical configurations of coolant mass exit gives the following results; (1) in order to increase the overall effectiveness of coolant mass injection, the second injection should be located in the upstream vicinity of the peak point of the adiabatic wall temperature or the heat transfer distributions, (2) if the total mass flow is kept constant, the width of coolant mass exit has negligible effect on the overall effectiveness pertinent to the heat transfer reduction. An experiment made under the adiabatic wall conditions indicates fairly good qualitative agreement with the numerical results. Finally, it is suggested that, under the condition of constant coolant mass flow, the effectiveness of the local mass injection cooling is superior to the transpiration cooling. | |||||||
| 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: SA2400794000 | |||||||
