@techreport{oai:jaxa.repo.nii.ac.jp:00002144,
 author = {上野, 真 and 赤塚, 純一 and Ueno, Makoto and Akatsuka, Junichi},
 month = {Feb},
 note = {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},
 title = {Application of the wake integral method to CFD data},
 year = {2008}
}