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亜音速および遷音速における二次元振動翼面上の非定常圧力分布の測定
https://jaxa.repo.nii.ac.jp/records/44754
https://jaxa.repo.nii.ac.jp/records/44754f2615c12-8477-419d-b840-dbd002f082d0
名前 / ファイル | ライセンス | アクション |
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naltr00501.pdf (3.8 MB)
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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 | 亜音速および遷音速における二次元振動翼面上の非定常圧力分布の測定 | |||||
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 | Measurements of Unsteady Pressure Distributions on an Oscillating Two-Dimensional Airfoil in Subsonic and Transonic Flow | |||||
著者 |
柳沢, 三憲
× 柳沢, 三憲× 菊地, 一雄× YANAGIZAWA, Mitsunori× KIKUCHI, Kazuo |
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著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所空気力学第一部 | ||||||
著者所属(英) | ||||||
en | ||||||
First Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
First 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-501 巻 501, p. 20, 発行日 1977-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The unsteady pressure distributions on an oscillating two-dimensional airfoil have been measured in the regions of subsonic and transonic flow, a Reynolds number range from 0.4×10(exp 6) to 2.0×10(exp 6) and a reduced frequency range from 0.01 to 0.1. Results of the experimental investigation are compared with those obtained by use of an incompressible theory and a doublet lattice method based on the lifting surface theory in the all Mach number ranges. In the subcritical regions the correction matrices to account for differences in the experimental and theoretical values have been calculated. In the supercritical regions the pressure deviations from the theoretical values due to the periodical motion of the shock are discussed and illustrated. Results, which are presented for supercritical flow with or without the shock, show that the transonic similarity law is valid in the unsteady reduced lift curve slope. | |||||
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: NALTR0501000 | |||||
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-501 |