@inproceedings{oai:jaxa.repo.nii.ac.jp:00005415,
 author = {黒滝, 卓司 and 住, 隆博 and 跡部, 隆 and 桧山, 淳 and Kurotaki, Takuji and Sumi, Takahiro and Atobe, Takashi and Hiyama, Jun},
 book = {宇宙航空研究開発機構特別資料: 第40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2008論文集, JAXA Special Publication: Proceedings fo 40th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2008},
 month = {Feb},
 note = {第40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2008. 会期: 2008年6月12日-6月13日. 会場: 東北大学片平キャンパス, A new numerical simulation approach is applied to the flow around an NACA0015 aerofoil with tonal noise generation including the natural transition on the suction side. The acoustic fields clearly show the radiation of sound waves from just after the trailing edge region. Numerical simulations also capture a separated region at the trailing edge on the pressure side. The linear stability analysis on the pressure side shows the possibility of the existence of T-S waves and the most unstable frequency up to the separation almost coincides with the peak frequency. The power spectrum distribution of stream wise velocity fluctuation clearly indicates that the generation of T-S waves on the pressure side is strongly relevant to the determination mechanism of the selection of peak frequency of the tonal edge noise and that the selfexcited feedback mechanism exists between just after the stagnation point at the leading edge and the trailing edge region., 形態: カラー図版あり, 資料番号: AA0064303013, レポート番号: JAXA-SP-08-009},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {NACA0015周りのtrailing edge noiseの数値シミュレーション},
 volume = {JAXA-SP-08-009},
 year = {2009}
}