| 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 Investigation of a Two-Dimensional Hybrid Laminar Flow Control Airfoil at High Subsonic Flow Part 1:Aerodynamic Characteristic of a Basic Airfoil NLAM78 |
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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 |
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その他のタイトル |
高亜音速流における二次元ハイブリッド層流制御翼の研究 (その1)基本翼型NLAM78の空力特性 |
| 著者 |
野中, 修
石田, 洋治
佐藤, 衛
神田, 宏
NONAKA, Osamu
ISHIDA, Yoji
SATO, Mamoru
KANDA, Hiroshi
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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（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-1076
巻 1076,
p. 25,
発行日 1990-08
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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 |
The present paper describes the experimentally determined aerodynamic characteristics of the NLAM 78 airfoil section, a natural-laminar airfoil designed in Ref.1, over the Mach number range 0.6 to 0.85 and angles of incidence from -1 to 4 as well as the Reynolds number 8, 16 and 32 million, respectively. The airfoil section was selected as the basic airfoil for the hybrid laminar flow control airfoil study which will be described in part 2. The test was executed in the NAL two-dimensional transonic wind tunnel with a test section of 0.3m×1.0m where measurements of the static pressure on the airfoil surfaces and the wake traverse were made. The test has shown that natural laminar airfoil characteristics are maintained for a flow condition of Mach numbers as high as 0.8 and angles of incidence up to 1deg, and that the lift to drag ratio L/D for the condition takes very high values of 72～85 depending on the Reynolds number. Also it shows that for the flow condition the drag divergence Mach number is about 0.82 and drag creep phenomena are rarely observed. Comparison with the flight data given in Ref.1 shows quite satisfactory agreement. Also comparison with some supercritical airfoil with almost the same thickness ratio as the present airfoil confirms the superiority of the aerodynamic characteristics of the NLAM 78 airfoil. |
| 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 |
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内容記述 |
資料番号: NALTR1076000 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL TR-1076 |
naltr01076.pdf (1.9 MB)
