Mitsubishi Heavy Industries Co.Ltd.
Mitsubishi Heavy Industries Co.Ltd.
National Aerospace Laboratory
Japan Aircraft Development Corporation
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory SP-9
巻
9
ページ
141 - 150
発行年
1988-12
抄録（英）
The rapid progress of the computational aerodynamics enables us to analyze airflow with viscous calculation instead of with invisid one. In two-dimensional application, we have already validated its effectiveness in comparison with wind tunnel testing and put it into practical stage. In three-dimensional application, the wing-body configulation has been also done. This paper presents a validative discussion of the panel method toward the analysis about the complete aircraft, including the calculation of the sting interference, which is indispensable to wind tunnel testing. The results indicate that the panel method is valid in the subsonic region and that the sting makes up wash flow.
遷音速全機形状まわりのパネル法計算と風洞試験の比較
nalsp0009021.pdf
(1.95MB)
