Pohang University of Science Technology Department of Mechanical Engineering
Pohang University of Science Technology Department of Mechanical Engineering
著者所属（英）
Pohang University of Science Technology Department of Mechanical Engineering
Pohang University of Science Technology Department of Mechanical Engineering
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
巻
46
ページ
301 - 306
発行年
2000-12
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 7-9 Jun. 2000 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 7-9 Jun. 2000 Tokyo Japan
As a step to develop an accurate solution technique, the grid-refined multi-block system in parallel computing was used to solve two-dimensional unsteady Navier-Stokes equations with Boldwin-Lomax turbulence modeling. Flow fields around NACA0012 on several conditions were solved to show the effectiveness of this method by comparing several aerodynamic coefficients with experimental data. In the first part, the solver was validated with steady/unsteady test cases to compare the results with experimental data. Flow fields around NACA0012 airfoil with pitching and/or plunging motions were analyzed by solving two-dimensional unsteady compressible Navier-Stokes equations. An unsteady flow field of the oscillatory airfoil was solved and compared with experimental data. Grids were refined near the airfoil and the wake region following the shedding vortex trace to reduce the numerical dissipation and multi-block grids with Zonal boundary were used for efficient calculation using parallel computing. In the second part, flow interactions between the wake and the airfoil were solved. The shedding vortex induced from the oscillating airfoil was applied as inflow condition of the following airfoil using periodic boundary conditions, which is a simplified two-dimensional model of a helicopter rotor blade at the mid-span section. The induced wake of the pitching airfoil, which was affected by the following airfoil, was used with various grid systems, so that the refined grid was shown to be effective in reducing the numerical dissipation.
Study on blade wake interaction using grid refinement method
nalsp0046054.pdf
(2.5MB)
