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Some Experimental Investigations on Transonic Flutter Characteristics of Thin Plate Wing Models with Sweptback and Tapered Tips
https://jaxa.repo.nii.ac.jp/records/44939
https://jaxa.repo.nii.ac.jp/records/44939f3e22b02-a350-45da-86f5-bb5b98dcc917
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00682.pdf (3.3 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 | Some Experimental Investigations on Transonic Flutter Characteristics of Thin Plate Wing Models with Sweptback and Tapered Tips | |||||||||
| 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 | |||||||||
| その他のタイトル | ||||||||||
| その他のタイトル | 先端後退翼の遷音速フラッタ特性に関する実験的研究 | |||||||||
| 著者 |
中井, 暎一
× 中井, 暎一
× NAKAI, Eiichi
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所機体第二部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Second 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 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-682 巻 682, p. 46, 発行日 1981-09 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Some experimental investigations on the transonic flutter characteristics have been conducted using thin plate cantilevered wing models with sweptback tapered tips, which were elastically supported at the root, in the NAL 0.6m×0.6m transonic blowdown wind tunnel for flutter testing in the range of Mach numbers from 0.804 to 1.171. The wing models have the tip planform of sweptback angels of 35deg at the leading edge and 30deg at 1/4 chord line, and an aspect ratio of 1.017 and a taper ratio of 0.6. It is concluded that the flutter boundaries of the wing models have been obtained and the boundaries expressed by the “experimental flutter speed coefficient” are characterised as having minimum values at around Mach number 1.0. It is also concluded that the considerable increase in the flutter instability area is caused by the decrease in the stiffness of the elastic support at the root of the model. | |||||||||
| 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: NALTR0682000 | |||||||||
| 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-682 | |||||||||
