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吸い込みのある2次元自然層流翼の高亜音速、高Re数風洞試験
https://jaxa.repo.nii.ac.jp/records/41189
https://jaxa.repo.nii.ac.jp/records/411891a6ffb71-1639-4d7f-b91e-baa3296a007c
名前 / ファイル | ライセンス | アクション |
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naltr01204.pdf (1.2 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 | 吸い込みのある2次元自然層流翼の高亜音速、高Re数風洞試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流制御実験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層吸い込み | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 自然層流翼型 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 2次元風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高レイノルズ数風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷音速風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ハイブリッド層流制御翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層遷移 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風試模型表面粗さ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 多孔壁吸い込み | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 多溝壁吸い込み | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 静圧分布計測 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar flow control experiment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer suction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | natural laminar flow airfoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | two dimensional wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | high Reynolds number wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transonic wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hybrid laminar flow airfoil | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer transition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel model surface roughness | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | perforated wall suction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | slotted wall suction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | static pressure measurement | |||||
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 | High subsonic and high Reynolds number wind tunnel tests of two-dimensional natural-laminar-flow airfoils with suction boundary layer control | |||||
著者 |
野口, 正芳
× 野口, 正芳× 佐藤, 衛× 神田, 宏× 石田, 洋治× Noguchi, Masayoshi× Sato, Mamoru× Kanda, Hiroshi× Ishida, Yoji |
|||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
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 巻 1204, p. 1-14, 発行日 1993-05 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 吸い込みのある場合とない場合との抵抗特性を比較するため、多溝性、多孔性および固体面の3種類の表面をもつ自然層流翼型模型につき高亜音速、高レイノルズ数での風洞試験を行った。マッハ数は0.60から0.85まで、レイノルズ数は6×10{6}から20×10{6}までの範囲とした。試験結果は、気流の乱れ、吸込み用溝や孔の存在などの層流化を妨げる要因があるにも拘わらず、吸い込みにより約10%の抵抗減少が得られることを示した。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Wind tunnel tests in high subsonic and high Reynolds number flows were conducted using slotted, perforated, and solid-surface NLF (Natural Laminar Flow) airfoils to compare their drag characteristics with and without suction. The Mach number was varied from 0.6 to 0.85 and the Reynolds number from 6 to 20 million. The results show that a net drag reduction of about 10 percent was attained by suction despite the presence of severe adverse effects against laminarization in the wind tunnel test such as free-stream turbulence and roughness effects of suction holes or slots. | |||||
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: AA0004219000 | |||||
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-1204 |