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Aerodynamic analysis of helicopter rotor by coupling of CFD and trim calculation
https://jaxa.repo.nii.ac.jp/records/37158
https://jaxa.repo.nii.ac.jp/records/371585ce38539-a24e-4fef-9072-dff07f5288c6
名前 / ファイル | ライセンス | アクション |
---|---|---|
nalsp0037032.pdf (541.4 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aerodynamic analysis of helicopter rotor by coupling of CFD and trim calculation | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ヘリコプタロータ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 反復結合法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 揚力線理論 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力コード | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 非定常オイラコード | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前進飛行 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 降下飛行 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼面圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | BVI | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼渦干渉 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | BVI騒音 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | helicopter rotor | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | iterative coupling method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | lifting line theory | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic code | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | unsteady Euler code | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | forward flight | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | descending flight | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | blade surface pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | BVI | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | blade vortex interaction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | BVI noise | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
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 | ||||||
その他のタイトル | CFDおよびトリム計算の結合によるヘリコプタロータの空力解析 | |||||
著者 |
近藤, 夏樹
× 近藤, 夏樹× 辻内, 智郁× 中村, 英明× 青山, 剛史× 齊藤, 茂× Kondo, Natsuki× Tsujiuchi, Tomoka× Nakamura, Hideaki× Aoyama, Takashi× Saito, Shigeru |
|||||
著者所属 | ||||||
コミュータヘリコプタ先進技術研究所 | ||||||
著者所属 | ||||||
コミュータヘリコプタ先進技術研究所 | ||||||
著者所属 | ||||||
コミュータヘリコプタ先進技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Technology Institute of Commuter-Helicopter Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Technology Institute of Commuter-Helicopter Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Technology Institute of Commuter-Helicopter Ltd | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
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 37, p. 205-210, 発行日 1998-02 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 航空宇宙技術研究所 12-13 Jun. 1997 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 揚力線理論に基づく空力コードとCFD(数値流体力学)コード間の反復結合法を開発し、ヘリコプタロータの空力解析に適用した。本手法では、空力として包括的積分ロータコードCAMRAD2(Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics)を、CFDコードとして非定常オイラーコードを、それぞれ用いる。本手法を適用して、高速前進飛行および降下飛行条件下のロータ空力特性を計算した。高速前進飛行の場合、計算した翼面圧力分布は実験データと良く一致した。この場合について、矩形翼端形状のみならず、単純化修正翼端形状についても解析した。結合法は、修正翼端形状の計算に必要であることが示された。降下飛行の場合、本手法を必要とすることも示した。さらに、BVI(翼渦干渉)騒音音圧を計算した。結合法は、降下飛行の場合におけるBVI騒音の予測に必ずしも必要ではないことが示唆された。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An iterative coupling method between an aerodynamic code based on the lifting-line theory and a Computational Fluid Dynamics (CFD) code is developed and applied to the aerodynamic analysis of helicopter rotor. In this method, a comprehensive integral rotor code, CAMRAD 2 (Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics), and an unsteady Euler code are used as the aerodynamic and the CFD code respectively. This method is applied to the calculation of rotor aerodynamics in a high-speed forward flight condition and a descending flight condition. The calculated pressure distributions on the blade surface are in good agreement with experimental data in the high-speed forward flight case. In this case, analyses are conducted not only for a rectangular tip shape but also for simply modified tip shapes. It is indicated that the coupling method is required for the calculation of modified tip shapes. In the descending flight case, it is also shown that the present method is required. In addition, the acoustic pressure of Blade-Vortex Interaction (BVI) noise is calculated. It is indicated that the coupling method is not always required for the prediction of BVI noise in this case. | |||||
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: AA0001433032 | |||||
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-37 |