JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63909000.pdf4.13 MB
titleApplication of the wake integral method to CFD data
Other TitleApplication of the wake integral method to CFD data
Author(jpn)上野 真; 赤塚 純一
Author(eng)Ueno, Makoto; Akatsuka, Junichi
Author Affiliation(jpn)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; 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
Author Affiliation(eng)Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology; Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Issue Date2008-02-29
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2008-02-29
Languageeng
AbstractThe 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.
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。
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordsaircraft wake; wake integral method; aerodynamic force; three dimensional model; aerodynamic characteristic; aerodynamic drag; computational fluid dynamics; body-wing configuration; rectangular wing; 航空機後流; 後流積分法; 流体力; 3次元モデル; 空力特性; 空力抵抗; 計算流体力学; 胴翼構成; 矩形翼
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0063909000
Report NoJAXA-RR-07-030E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/45797


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