@inproceedings{oai:jaxa.repo.nii.ac.jp:00004877,
 author = {池田, 友明 and 高木, 正平 and Ikeda, Tomoaki and Takagi, Shohei},
 book = {宇宙航空研究開発機構特別資料: 「境界層遷移の解明と制御」研究会講演論文集（第43回・第44回), JAXA Special Publication: Proceedings of the 43rd and 44th JAXA Workshops on "Investigation and Control of Boundar-Layer Transition"},
 month = {Feb},
 note = {第43回（2008年10月2日-10月3日）「境界層遷移の解明と制御」研究会; 第44回（2009年3月26日-3月27日）「境界層遷移の解明と制御」研究会, 43rd JAXA Workshops on "Investigation and Control of Boundar-Layer Transition" (October 2-3, 2008) ; 44th JAXA Workshops on "Investigation and Control of Boundar-Layer Transition" (March 26-27, 2009), Aerodynamic noise generated from 2-D airfoils is of interest in conjunction with the development of Karman-vortex shedding in the wake region. In this study, the computational aspects are discussed to reproduce the trailing-edge noise using acoustic analogies, based on the flow field obtained by a compressible flow solver with higher-order numerical schemes. The comparative study indicates that less-expensive acoustic analogies fail in representing the acoustically non-compact sound source with incompressible flow field However, by using a compressible near-field solution, the FW-H equation successfully predicts the far-field sound pressure directivity, for an accurate pressure fluctuation is provided at the airfoil surface., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064575001, レポート番号: JAXA-SP-09-014},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {低Re数の二次元翼から発生する空力音について: 数値手法},
 volume = {JAXA-SP-09-014},
 year = {2010}
}