| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
MEASUREMENT OF AERODYNAMIC CHARACTERISTICS OF A HANG-GLIDER-WING BY GROUND RUN TESTS USING A TEST VEHICLE |
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言語 |
en |
| 言語 |
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|
言語 |
eng |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル |
|
|
その他のタイトル |
走行実験によるハンググライダ翼の空力特性について |
| 著者 |
穂積, 弘毅
古茂田, 真幸
小野, 孝次
塚野, 雄吉
HOZUMI, Koki
KOMODA, Masaki
ONO, Takatsugu
TSUKANO, Yukichi
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| 著者所属 |
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航空宇宙技術研究所飛行実験部 |
| 著者所属 |
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航空宇宙技術研究所飛行実験部 |
| 著者所属 |
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航空宇宙技術研究所飛行実験部 |
| 著者所属 |
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航空宇宙技術研究所飛行実験部 |
| 著者所属（英） |
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en |
|
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
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|
en |
|
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
|
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|
en |
|
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
|
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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-953
巻 953,
p. 23,
発行日 1987-11
|
| 抄録（英） |
|
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内容記述タイプ |
Other |
|
内容記述 |
In order to investigate longitudinal force and moment characteristics of a hang-glider-wing, ground run tests were conducted using a test vehicle. A hang-glider-wing was installed on a test vehicle using a six-components-balance for wind tunnel use. Aerodynamic force and moment were measrued during the vehicle run at various constant speeds. Geometrical twist distribution along the wing span was recorded as well. Measured force and moment data were corrected for possible ground effect and upwash effect due to movement of the vehicle. The lift curve slope was about 23％ smaller than that predicted by theory for a rigid wing of the same geometry. An abrupt increase in the pitching moment was measured as CL decreased from positive to negative. These particular features indicate that aeroelastic deformations affect the aerodynamic characteristics of hang-gliders and/or motor-hang-gliders are mandatory for their flight safety. Using the Moriya method, aeroelastic camber variations at typical spanwise stations were estimated for each combination of dynamic pressure and section angle of attack. Applying the Weissinger method, lift and pitching moment characteristics were analyzed twist distributions. By comparing these analyses with the measured data, geometrical deformations of the flexible wing were elucidated. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0389-4010 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0953000 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-953 |
naltr00953.pdf (2.1 MB)
