Mitsubishi Heavy Industries Co.Ltd.
Mitsubishi Heavy Industries Co.Ltd.
National Aerospace Laboratory
National Aerospace Laboratory
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-7
巻
7
ページ
33 - 38
発行年
1986-12
抄録（英）
Computational aerodynamics as an aircraft design tool now stands shoulder to shoulder with wind tunnel testing due to the rapid progress of computer software and hardware. In particular, the Navier-Stokes computation which has been researched re-cently, enables us to analyze airflow not only at a design point but also in off-design regions. NSFOIL, the high Reynolds number transonic airfoil analysis code developed at NAL, has been verified by comparing computations based on the code with results obtained from actual wind tunnel tests. This paper presents a validative discussion of the NSFOIL code in the region of low speed and high attack angle. The computational results are compared with results of wind tunnel tests and the vortex method, which is a separated flow analysis method, to in-vestigate the validity of the code and to further the development of future improvements. NSFOIL is found to be able to predict non-linear characteristics, in which conventional numerical methods are powerless. There is still some room for improvement to be able to calculate an exact stall angle.
二次元粘性流計算ソフトウェアの実用化
nalsp0007004.pdf
(719.4KB)
