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境界要素法による前縁はく離渦の効果を入れたデルタ翼の空力計算
https://jaxa.repo.nii.ac.jp/records/37856
https://jaxa.repo.nii.ac.jp/records/378564f915a20-9fe6-4f21-8d6b-4ca2e73876ad
名前 / ファイル | ライセンス | アクション |
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nalsp0027019.pdf (445.5 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 境界要素法による前縁はく離渦の効果を入れたデルタ翼の空力計算 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | デルタ翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スレンダー翼理論 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前縁剥離渦 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界要素法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 高次近似パネル法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 渦追跡 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ポテンシャル流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 物体の周りの流れ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 後退翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流れ場 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層剥離 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前縁 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | delta wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | slender wing theory | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | leading edge separation vortex | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary element method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | higher order panel method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | vortex tracking | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | potential flow calculation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow around body | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | swept wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic airplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flow field | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer separation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | leading edge | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Calculation for aerodynamic characteristics on delta wing with leading-edge separated vortex effect using boundary element method | |||||
著者 |
菊地, 勝浩
× 菊地, 勝浩× 菊池, 秋広× 柳澤, 三憲× Kikuchi, Katsuhiro× Kikuchi, Akihiro× Yanagizawa, Mitsunori |
|||||
著者所属 | ||||||
東京理科大学 大学院 | ||||||
著者所属 | ||||||
東京理科大学 大学院 | ||||||
著者所属 | ||||||
東京理科大学 理学部 | ||||||
著者所属(英) | ||||||
en | ||||||
Science University of Tokyo Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Science University of Tokyo Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Science University of Tokyo Faculty of Science | ||||||
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特別資料 en : Special Publication of National Aerospace Laboratory 巻 27, p. 153-158, 発行日 1994-12 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | デルタ翼のまわりの流れの特性に関する計算方法を述べた。高後退角の翼がある程度以上の迎角を持つときは前縁から流れが剥離する。デルタ翼はスレンダーボディと考え得るのでスレンダーボディ理論を用いた。まず3次元翼形状から2次元断面形を切り出し、つぎに渦追跡法を用いて前縁剥離渦の位置と強さを求める。前縁剥離渦の効果を含めるためのモデルを提案した。本方法を用いてデルタ翼の空力特性を求め、実験結果と比較してよい一致をみた。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The method which allows the calculation of the characteristics for flow around a delta wing is described. Flow separations are certain to occur from the leading-edge on highly swept wings at moderate-to-high angles of attack. Since delta wing is considered as slender body, slender body theory is resorted. So first, two-dimensional cross sections are generated by slicing three-dimensional model and the position and strength of leading-edge separation vortices is determined using vortex tracking method. In order to include the effect of leading-edge separation vortex a model is proposed. Some aerodynamic coefficients of delta wing are obtained from the present method and comparisons between numerical and experimental results show good agreement. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0004174019 | |||||
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 SP-27 |