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翼型を過ぎる遷音速ポテンシャル流の厳密解法
https://jaxa.repo.nii.ac.jp/records/44631
https://jaxa.repo.nii.ac.jp/records/44631d0ef24fa-c41f-4fa3-a2e2-c83896898920
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00383.pdf (2.1 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 | 翼型を過ぎる遷音速ポテンシャル流の厳密解法 | |||||||||
| 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 Exact Solution for Transonic Potential Flow Past Aerofoil Sections | |||||||||
| 著者 |
高梨, 進
× 高梨, 進
× TAKANASHI, Susumu
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所空気力学第二部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Second Aerodynamics 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-383 巻 383, p. 29, 発行日 1974-08 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | A hodograph method is developed for obtaining exact solutions of transonic potential flow around lifting aerofoils. The procedure of constructing compressible flows from incompressible flows is based on those of Lighthill and Nieuwland. In the present theory, however, the complex hodograph potential representing the starting incompressible flow is divided into two parts; one is a simple function which has the desired singularity of dipole and vortex at the point corresponding to infinity in the physical plane, and the other is chosen to be a regular function so that the total function represents a flow around a pseudo-elliptical body. This splitting of the solution has many advantages from the mathematical and computational points of view. The geometrical and aerodynamical characteristics of the resulting aerofoils in the compressible flow are controlled by a number of parameters. A family of practically interesting transonic shock-free aerofoils has been computed by changing the values of these parameters. An aerofoil of this family was tested in the wind tunnel to compare with the theoretical prediction. | |||||||||
| 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: NALTR0383000 | |||||||||
| 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-383 | |||||||||
