@inproceedings{oai:jaxa.repo.nii.ac.jp:00006451,
 author = {榎本, 俊治 and 今村, 太郎 and 山本, 一臣 and Enomoto, Shunji and Imamura, Taro and Yamamoto, Kazuomi},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004},
 month = {Mar},
 note = {In order to simulate acoustic noise of high lift devices, a Large Eddy Simulation code for sound source simulation was developed. The higher order compact scheme by Lele was utilized for spatial discretization. Vortical flow around NACA0012 wing tip was computed by the LES code, and the results were compared with the experimental data including Particle Image Velocimetry data that were obtained from the wind tunnel experiment performed at ISTA/JAXA. Obtained time-average results showed qualitatively good agreement with PIV results. But the unsteady LES data overestimates low-frequency pressure fluctuation near the leading edge on the tip surface compare to the data from unsteady pressure sensor., 資料番号: AA0048469011, レポート番号: JAXA-SP-04-012},
 pages = {69--74},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {NACA0012翼端渦の乱流数値解析},
 volume = {JAXA-SP-04-012},
 year = {2005}
}