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Application of the wake integral method to CFD data
https://jaxa.repo.nii.ac.jp/records/2144
https://jaxa.repo.nii.ac.jp/records/214460878964-ecf8-4c45-8988-25e2aaffde7c
名前 / ファイル | ライセンス | アクション |
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63909000.pdf (4.2 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Application of the wake integral method to CFD data | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 航空機後流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 後流積分法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流体力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 3次元モデル | |||||
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 | 空力抵抗 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 胴翼構成 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 矩形翼 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aircraft wake | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wake integral method | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic force | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | three dimensional model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic drag | |||||
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 | body-wing configuration | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rectangular wing | |||||
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 | |||||
著者 |
上野, 真
× 上野, 真× 赤塚, 純一× Ueno, Makoto× Akatsuka, Junichi |
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著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構研究開発報告 en : JAXA Research and Development Report 巻 JAXA-RR-07-030E, 発行日 2008-02-29 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 物体後流内部の物理量を積分して抵抗と揚力を算出する手法(Wake Integral Method)を3次元CFD(Computational Fluid Dynamics)データに適用し、飛行機の各要素が抵抗全体に及ぼす影響の度合いの定量的な評価を行った。この手法では抵抗を発生要因によってProfile DragとInduced Dragに分解し、さらに空気力の定量的な分布を得ることができる。従って、CFDにおいても風洞試験データにおいても同様に抵抗発生要因を特定し、設計にフィードバックすることが期待できる。本研究ではNACA0012断面を有する矩形翼と翼胴形態であるDLR F6模型に対する解析を行い、解析結果から得られる知見について考察を行った。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The wake integral method, a method that analyzes aerodynamic forces by integral in the wake of a model, was applied to three-dimensional CFD (Computational Fluid Dynamics) data and a quantitative assessment of aerodynamic forces produced by airplane elements was performed. The method allows the drag force exerted on a body to be decomposed into profile and induced drag components, and provides their distributions. By using this method, a designer can expect to obtain insight into aerodynamic drag production factors from CFD data and wind tunnel wake traverse data. In this study, CFD spatial data of a rectangular NACA0012 section wing and the DLR F6 wing-body model were analyzed and the insights gained into the aerodynamic force distributions and drag were examined. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-1113 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA1192675X | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063909000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-RR-07-030E |