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title差分格子ボルツマン法によるBVIの数値解析
Other TitleNumerical simulation of blade-vortex interactions using the FDLBM
Author(jpn)田村 明紀; 蔦原 道久; 片岡 武; 青山 剛史; Yang, Choongmo
Author(eng)Tamura, Akinori; Tsutahara, Michihisa; Kataoka, Takeshi; Aoyama, Takashi; Yang, Choongmo
Author Affiliation(jpn)神戸大学 大学院自然科学研究科; 神戸大学 大学院自然科学研究科; 神戸大学 大学院自然科学研究科; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Kobe University Graduate School of Science and Technology; Kobe University Graduate School of Science and Technology; Kobe University Graduate School of Science and Technology; Japan Aerospace Exploration Agency Institute of Aerospace Technology; Japan Aerospace Exploration Agency Institute of Aerospace Technology
Issue Date2008-02-29
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication title第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集
Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007
Start page39
End page44
Publication date2008-02-29
Languagejpn
AbstractParallel blade-vortex interactions have been calculated using the finite difference lattice Boltzmann method of the compressible Euler model. The perturbed discrete Boltzmann equation based on a prescribed vortex method has been proposed in order to prevent a vortex from diffusing by numerical dissipation. The discretization of the governing equation is based on a second order accurate explicit Runge-Kutta time integration and a fifth order accurate upwind scheme which includes additional terms to capture shock waves clearly. Transonic flow around an airfoil without vortexes has been simulated to validate the perturbed discrete Boltzmann equation system. A surface pressure distribution and pressure contour lines around the airfoil have been compared with other numerical data, and good agreements have been obtained. As a simple model of parallel blade-vortex interaction, two-dimensional blade-vortex interaction has been calculated using the proposed numerical method. An instantaneous pressure coefficient, a time history of a lift coefficient and patterns of acoustic waves have been compared with other numerical results, and agreed with them very well. Mechanism of noise generation has been also captured from numerical results. Three-dimensional calculations of parallel blade-vortex interaction have been performed using the present numerical procedure. Time variations of surface pressure distributions have been compared with Euler calculation and experimental data, and good agreements have been obtained.
DescriptionJAXA Special Publication
宇宙航空研究開発機構特別資料
Keywordsaerodynamic noise; heliport; BVI noise; blade-vortex interaction; computerized simulation; finite element method; pressure distribution; two dimensional model; noise reduction; Euler equation of motion; compressible fluid; 空力騒音; ヘリポート; BVI騒音; 翼渦干渉; 計算機シミュレーション; 有限要素法; 圧力分布; 2次元モデル; 騒音低減; オイラー運動方程式; 圧縮性流体
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
SHI-NOAA0063742007
Report NoJAXA-SP-07-016
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/34239


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