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大迎角翼型回りの遷音速流の数値解析
https://jaxa.repo.nii.ac.jp/records/43263
https://jaxa.repo.nii.ac.jp/records/43263ad9f4c51-1427-4a78-83b7-2894315c9e6d
名前 / ファイル | ライセンス | アクション |
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nalsp0008010.pdf (837.9 kB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 大迎角翼型回りの遷音速流の数値解析 | |||||
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 | Computation of Flow around NACA0012 Airfoil at High Angle of Attack | |||||
著者 |
信太, 良文
× 信太, 良文× 桑原, 邦郎× Shida, Yoshifumi× Kuwahara, Kunio |
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著者所属 | ||||||
計算流体力学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
The Institute of Computational Fluid Dynamics | ||||||
著者所属(英) | ||||||
en | ||||||
The Institute of Space and Astronautical Science | ||||||
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特別資料 en : Special Publication of National Aerospace Laboratory SP-8 巻 8, p. 73-80, 発行日 1987-11 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Transonic flow around an NACA0012 airfoil at high angle of attack is simulated by solving the two-dimensional Navier-Stokes equations. The block pentadiagonal matrix scheme is employed. Periodic phenomena of shock-wave vortex interaction are observed. For comparison, computation of subsonic flow has been done. Small vortices are observed between the leading edge and the center of the chord. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALSP0008010 | |||||
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 SP-8 |