Application of the wake integral method to CFD data

Material type: 文書・図像類

Author: 上野, 真ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2008-02-29

Material Format: Digital

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Note (General)：: 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Profi...

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Material Type: 文書・図像類
Title: Application of the wake integral method to CFD data
Author/Editor: 上野, 真
赤塚, 純一
Ueno, Makoto
Akatsuka, Junichi
Author Heading: 上野, 真
赤塚, 純一
Ueno, Makoto
Akatsuka, Junichi
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2008-02-29
Publication Date (W3CDTF): 2008-02-29
Periodical title: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
No. or year of volume/issue: JAXA-RR-07-030E
Volume: JAXA-RR-07-030E
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: eng
Subject Heading: 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
aircraft wake
wake integral method
aerodynamic force
three dimensional model
aerodynamic characteristic
aerodynamic drag
computational fluid dynamics
body-wing configuration
rectangular wing
Target Audience: 一般
Note (General): 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。
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.
資料番号: AA0063909000
レポート番号: JAXA-RR-07-030E
Access Restrictions: 限定公開
Periodical Title (NCID): AA1192675X
https://ci.nii.ac.jp/ncid/AA1192675X
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ