Study on blade wake interaction using grid refinement method

• Material Type: 規格・テクニカルリポート類
• Title: Study on blade wake interaction using grid refinement method
• Author/Editor: Yang, Choongmo; Baek, Jehyun
• Author Heading: Yang, Choongmo; Baek, Jehyun
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 2000-12
• Publication Date (W3CDTF): 2000-12
• Alternative Title: グリッド細密法によるブレード後流相互作用の研究
• Periodical title: 航空宇宙技術研究所特別資料
• No. or year of volume/issue: 46
• Volume: 46
• Pages: 301-306
• ISSN (Periodical Title): ISSN : 0289-260X
• Text Language Code: eng
• Subject Heading: ブレード後流相互作用; BWI; 格子細密法; 数値シミュレーション; 非定常流; ナビエ-ストークス方程式; マルチブロック; 並列計算; NACA0012; ヘリコプタ・ロータブレード; 振動翼型; 周期的境界条件; ピッチング; プランジング; blade wake interaction; grid refinement method; numerical simulation; unsteady flow; Navier Stokes equation; multi block; parallel computation; helicopter rotor blade; oscillatory airfoil; periodic boundary condition; pitching; plunging
• Target Audience: 一般
• Note (General): 航空宇宙技術研究所 7-9 Jun. 2000 東京 日本; 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.; 資料番号: AA0028635054; レポート番号: NAL SP-46
• Access Restrictions: インターネット公開
• Periodical Title (NCID): AN10097345; https://ci.nii.ac.jp/ncid/AN10097345
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ

• Summary, etc.: 高精度解法を開発するための1段階として、Boldwin-Lomax乱流モデルで2次元非定常ナビエ-ストークス方程式を解くために、並列計算でグリッド密度の高い、多ブロック系を使用した。NACA0012翼型の周りの流れ場をいくつかの条件に対して解いた。その結果は、各条件の下で空力係数が実測と一致し、この...