@inproceedings{oai:jaxa.repo.nii.ac.jp:00004922,
 author = {今村, 太郎 and 平井, 亨 and 横川, 譲 and 榎本, 俊治 and 山本, 一臣 and Imamura, Taro and Hirai, Tohru and Yokokawa, Yuzuru and Enomoto, Shunji and Yamamoto, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 第41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2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, Three-dimensional unsteady flow around NACA0012 wingtip is simulated numerically to investigate the cause of flap-edge noise generation. The vortical flow structures around the NACA0012 are known to be similar to that of a flap-edge. Therefore, it is assumed that noise generation mechanism is similar as well, although its geometry is simpler than a flap-edge. Since the Reynolds number of the flow is high, a zonal LES/RANS hybrid method is used to reduce the overall computational cost. The power spectral density of the pressure coefficient is compared with the experiment, and several issues regarding, the number of sub iteration for implicit time integration, sensitivity to Smagorinsky constant, grid overlap points at block-block interface, and grid resolution, are discussed. Subsequently, two longitudinal vortical structures around the wingtip, that show different characteristics, are investigated to understand its generation mechanism., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672024, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {NACA0012切り落とし翼端から発生する渦のLES解析},
 volume = {JAXA-SP-09-011},
 year = {2010}
}