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Measurements of the Aerodynamic Derivatives of an Oscillating Biconvex-Flat Airfoil in Supersonic Flow at Mach Number 2 to 3
https://jaxa.repo.nii.ac.jp/records/44296
https://jaxa.repo.nii.ac.jp/records/44296eefa9e81-b27b-4a15-9971-fc8c39b11580
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr0057t.pdf (3.4 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 | Measurements of the Aerodynamic Derivatives of an Oscillating Biconvex-Flat Airfoil in Supersonic Flow at Mach Number 2 to 3 | |||||||||
| 言語 | en | |||||||||
| 言語 | ||||||||||
| 言語 | eng | |||||||||
| 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 | |||||||||
| 著者 |
ISHII, Takao
× ISHII, Takao
× YANAGIZAWA, Mitsunori
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| 著者所属（英） | ||||||||||
| en | ||||||||||
| National Aeronautical Laboratory First Aerodynamics Division | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Nippon Oil Seal Industry Co., Ltd., First Aerodynamics Division, National Aeronautical 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 |
en : Technical Report of National Aerospace Laboratory TR-57T 巻 57T, p. 17, 発行日 1964-01 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The aerodynamic derivatives of a biconvex-flat airfoil (thickness ratio of 10 per cent), and double-wedge airfoils (thickness ratios of 10, 15, 20 percent), performing pitching oscillation in supersonic flow at the range of Mach number2-3, were measured and compared with the linearized theory, piston theory and Van Dyke's nonlinear theory which includes the effect of the airfoil thickness. The tested reduced frequency range was 0.01-0.05 and the Reynolds number range was 2.8 by 10(6)-3.6 by10(6) based on the chord length. In spite of the existence of the detached shock wave in front of the leading edge of the biconvex-flat airfoil, all experimental results agree quite well with the nonlinear theory. Schlieren photographs were taken in order to observe the flow field around the airfoils. | |||||||||
| 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: NALTR0057T000 | |||||||||
| 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-57T | |||||||||
