| 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 |
An Experimental Study of a Three-Dimensional Swept-Back Wing Suction Laminar-Flow-Control |
|
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 |
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その他のタイトル |
三次元後退角LFC翼の風洞試験 |
| 著者 |
石田, 洋治
野口, 正芳
萱場, 重男
野中, 修
星野, 秀雄
ISHIDA, Yoji
NOGUCHI, Masayoshi
KAYABA, Shigeo
NONAKA, Osamu
HOSHINO, Hideo
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| 著者所属 |
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航空宇宙技術研究所空力性能部 |
| 著者所属 |
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航空宇宙技術研究所空力性能部 |
| 著者所属 |
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航空宇宙技術研究所空力性能部 |
| 著者所属 |
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航空宇宙技術研究所空力性能部 |
| 著者所属 |
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航空宇宙技術研究所空力性能部 |
| 著者所属（英） |
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en |
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Aircraft Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aircraft Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aircraft Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
|
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Aircraft Aerodynamics Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
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Aircraft Aerodynamics 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-1072
巻 1072,
p. 23,
発行日 1990-07
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
A wind tunnel test of a three-dimensional swept-back wing with suction laminar-flow-control was executed to investigate the drag reduction effect of the LFC under various test conditions. The wing model has a hybrid suction surface which consists of a porous surface with very fine holes from near the leading edge to 25％ chord and a slotted surface with a large number of fine slots from 25％ chord to 80％ chord. Total drag CDT, which is defined as the sum of the wake drag and the equivalent drag, was measured for various suction quantities. Application of the optimum suction quantities, which were determined so as to delay the natural transition points to 90％ chord with the minimum total suction quantity for each test conditon, gives a fairly large drag reduction(about 40％) compared with the no suction case for Reynolds numbers up to 3.6×10(exp 6). A suction applied only in the leading edge region also gives not a little drag reduction, but a suction in the rear part of the wing where the boundary layer flow is already turbulent has no effect on the drag reduction. It has been observed that when there is no suction the porous suction surface generates much earlier transitions than does the solid surface. As transition is a very important problem for practical application of LFC, further investigation will be required. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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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: NALTR1072000 |
| 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-1072 |
naltr01072.pdf (2.0 MB)
