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翼振れ限界内外に於ける非定常振動の問題に就て
https://jaxa.repo.nii.ac.jp/records/35352
https://jaxa.repo.nii.ac.jp/records/353521afedb9d-910f-44fe-a38e-f35f4817e29d
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA4146544.pdf (1.0 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 | 翼振れ限界内外に於ける非定常振動の問題に就て | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 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 | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | The Problem of Non-stationary Vibration for a Range below and beyond the Critical of Wing Flutter. | |||||||||
| 著者 |
井上, 隆介
× 井上, 隆介
× INOUE, Takasuke
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| 著者所属 | ||||||||||
| 妹澤研究室 | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 東京帝國大學航空研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Aeronautical Research Institute, Tokyo Imperial University | |||||||||
| 書誌情報 |
東京帝國大學航空研究所報告 en : Report of Aeronautical Research Institute, Tokyo Imperial University 巻 20, 号 271, p. 67-94, 発行日 1943-09 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The paper deals with the theory of a two-dimensional thin airfoil in oscillating motion in three degrees of freedom, namely, the translatory, the rotational motion about the flexural axis and the aileron motion about the hinge axis. In the first place, the equations of motion are solved in Heaviside's operational form, in which the Theodorsen's function that was shown in W. R. Sear's paper also manifests itself. As the result of using Heaviside's form, the paper is to deal with the transient state of the oscillating airfoil and is not restricted to the case of such a critical point of flutter as shown by a number of investigators, dealing merely with the problem of the steady harmonic state of motion. In numerical calculation, the Wagner's function, that is to say, the interpretation of the Theodorsen's function, is shown in a simple approximate expression. Using the solution of the problem, two cases are discussed, namely, (1) the effect of altitude, that is to say, the change of ratio of the wing density to air density, on flutter condition, and (2) the effect of the position of flexural axis and the distance between the flexural axis and the centre of gravitation on flutter condition. In every case the damping coefficients and the vibrational frequencies are moreover obtained. The result of investigation shows that (1) with increase of altitude the true (calculated) flutter speed increases, but the speed to be read in altimeter decreases; and that (2) with increase of mass-balance flutter speed increases anormously, but damping coefficients tend to maxima for a small over-balance. The change of damping coefficients and the vibrational frequencies are generally rather complicated, the detail of which will be shown in the paper. | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA00387631 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA4146544000 | |||||||||
