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Natural Vibration and Panel Flutter of Cylindrically Curved Panels
https://jaxa.repo.nii.ac.jp/records/44560
https://jaxa.repo.nii.ac.jp/records/44560500e1475-c139-49ab-8350-a27b6ff5156d
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr0315t.pdf (1.1 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | Natural Vibration and Panel Flutter of Cylindrically Curved Panels | |||||||||
| 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_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| 著者 |
松崎, 雄嗣
× 松崎, 雄嗣
× MATSUZAKI, Yuji
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所機体第一部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| First Airframe Division, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||
| 書誌情報 |
en : Technical Report of National Aerospace Laboratory TR-315T 巻 315T, p. 12, 発行日 1973-04 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Influences of in-plane boundary conditions and panel geometry on natural vibration and flutter characteristics of cylindrically curved panels, exposed to a supersonic flow parallel to the generators, are analyzed with the aid of Galerkin’s method within the framework of Reissner’s shallow shell theory. Almost all results are obtained by using twelve assumed modes, namely, a combination of the first six streamwise and the first two symmetrical spanwise modes. Convergence of flutter solutions is checked by taking the first ten streamwise modes at the most. The numerical results have revealed that influences of in-plane boundary conditions and panel geometry are much more complicated than previously reported. Since some results indicate that spanwise modal coupling due to the in-plane edge restraint yeilds coincidence of natural frequencies which has a detrimental effect on flutter boundary, omission of the higher spanwise modes in flutter analysis leads to erroneous results for such cases. Although the present analysis has limitation on choice of combinations of the in-plane boundary conditions, a general recommendation for flutter prevention of curved panels whose aspect ratio is about 1 is that the panels should be able to move freely along the spanwise direction at straight edges and be tangentially restrained at curved edges. Comparison between results predicted by the quasi-steady and the steady aerodynamic theories indicates that the static aerodynamic theory would provide a good prediction for flutter of such panels. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0315T000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-315T | |||||||||
