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Instability of Shock Wave on Thin Airfoil in High Subsonic Flow
https://jaxa.repo.nii.ac.jp/records/34610
https://jaxa.repo.nii.ac.jp/records/34610c5a1072d-dc83-4138-a896-d16df3b38a53
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2404863.pdf (6.1 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 | Instability of Shock Wave on Thin Airfoil in High Subsonic Flow | |||||||
| 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
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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 3, p. 39-118, 発行日 1961-03 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | Present paper gives the results of detailed experimental and theoretical investigations of oscillating shock wave on two-dimensional thin airfoil in high subsonic flow. The paper consists of three parts. In the first part are presented the detailed results of experimental investigation associated with instability of a surface shock wave in high subsonic flow. The results show that the phenomenon of instability of surface shock wave is rather critical and there exists a critical Mach number for which the shock wave becomes unstable when the boundary layer on the airfoil surface is laminar, while, for the turbulent boundary layer, the shock wave is quite stable. It is concluded that the laminar-interaction mechanism may play a role in exciting the shock oscillation. The second part is concerned with discussion on the construction of an oscillating flow field and its eigenvalue problem due to the interaction of a shock wave with a laminar boundary layer in order to give some theoretical explanations to the instability of surface shock wave in high subsonic flow. The effect of pressure gradient in the undisturbed inviscid flow outside the boundary layer is also examined in detail. The results show that there is a combination of frequency and shock strength for which a stable oscillation of the surface shock wave is preserved and the pressure gradient has a constribution to the decrease of the critical Mach number for instability of the shock wave. For the purpose of confirming the theoretical approach made in Part 2,the results of numerical computations made for the same airfoil as used in the present experiment are shown in Part 3 and they are compared with experimental data. The agreement between theory and experiment is fairly good. It is found that, for the biconvex circular-arc airfoil with thickness-chord ratio of 0.1,local Mach number critical for the shock oscillation is about 1.22,which is fairly insensitive to Reynolds number. | |||||||
| ISSN | ||||||||
| 収録物識別子タイプ | ISSN | |||||||
| 収録物識別子 | 0376-1061 | |||||||
| 書誌レコードID | ||||||||
| 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: SA2404863000 | |||||||
