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多翼素翼型の逆問題の解法
https://jaxa.repo.nii.ac.jp/records/44825
https://jaxa.repo.nii.ac.jp/records/4482538325a3f-34c4-4d7e-849d-aacd77224347
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00571.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 | 多翼素翼型の逆問題の解法 | |||||||||
| 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_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | An Inverse Method for the Design of Multi-Element Aerofoils | |||||||||
| 著者 |
重見, 仁
× 重見, 仁
× SHIGEMI, Masashi
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所新型航空機研究グループ | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| V/STOL Aircraft Research Group, 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-571 巻 571, p. 13, 発行日 1979-04 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | A design method is presented for single, as well as, multi-element aerofoils, which are intended to realize prescribed velocity distributions on the surface. The general framework of the theory depends on the panel method. An arbitrary shape of the wing section is assumed as a starting geometry and a row of vortices is distributed along its contour, whose strength is readily known from the prescribed velocity distribution. When the resultant velocity induced from the distributed vortices, together with that of uniform flow superposed, is calculated at each point on the surface, it is noticed that the velocity component normal to the surface does not generally vanish because of an inappropriate choice of the starting geometry. The modification of the geometry is then manipulated in the following way;the formula in the panel method, which relates the normal velocity to the wing geometry, can be developed into a Taylor series, in terms of the wing coordinates of the current tentative geometry. When the higher order terms are neglected, it leads to a linear relation between the normal velocity and the shift of the coordinate. Hence, calculated residual of the normal velocity can be transformed into the amount of local modification of the wing geometry. If the renewed geometry thus obtained is not yet adequate, the same procedure is repeated until good convergence is attained to the final geometry, by which the flow condition given at the outset is well satisfied. A few examples show that our method is quite satisfactory in designing objective aerofoil shapes accurately with no specific constrains. | |||||||||
| 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: NALTR0571000 | |||||||||
| 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-571 | |||||||||
