@inproceedings{oai:jaxa.repo.nii.ac.jp:00004713,
 author = {跡部, 隆 and 池田, 友明 and Atobe, Takashi and Ikeda, Tomoaki},
 book = {宇宙航空研究開発機構特別資料: 第42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2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42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2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, The unsteady aerodynamics of a two-dimensional NACA0006 airfoil are investigated at a low Reynolds number, directly resolving acoustic perturbations in subsonic flows. At a relatively low angle of attack, periodic vortex sheddings are reproduced, simultaneously generating a dipole sound from the trailing edge. By slightly altering inflow Mach number, the shedding frequency often changes drastically, presumably via the onset or offset of an acoustic feedback loop, which correlates an aerodynamic sound emission from the trailing edge, and an instability mechanism in the suction-side boundary layer of the foil. In this study, the phase difference between two different waves - an emitted sound wave and an induced instability wave, is statistically sampled and examined to clarify the on/off determination mechanism of the acoustic feedback loop., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967006, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {低Re数翼周り流れの境界層不安定と音響変動との相関について},
 volume = {JAXA-SP-10-012},
 year = {2011}
}