First Aerodynamics Division, National Aerospace Laboratory(NAL)
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報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-835
巻
835
ページ
27
発行年
1984-09
抄録（英）
A boundary element method for the evaluations of steady aerodynamic loads around complex configurations in subsonic flow has been developed using Green’s function. Morino described the form of the integral equation, which is transformed into a set of linear algebric equations. The velocity on the arbitrary point of the body surface is given by the derivative of the velocity potential on the point along the surface stream line. The purpose of this paper is to present a new paneling and derivative technique which can be applied to any complex configuration. To evaluate the derivative of velocity potential on the surface, the surface element is replaced with the circular arc, which is determined by three collocation points in adjoining panels. Aerodynamic quantities, such as pressure distributions, lift, pitching moment and drag of the actual airplane in compressible flow, are calculated as an example. Comparisons between numerical and experimental results show good agreement.
境界要素法を用いた亜音速流中の三次元揚力物体の空力特性の計算
naltr00835.pdf
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