@inproceedings{oai:jaxa.repo.nii.ac.jp:00038194,
 author = {石井, 克哉 and 鈴木, 智 and 安達, 静子 and Ishii, Katsuya and Suzuki, Satoshi and Adachi, Shizuko},
 book = {航空宇宙技術研究所特別資料: 境界層遷移の解明と制御研究会講演論文集　第29回・第30回, Special Publication of National Aerospace Laboratory: Proceedings of the 29th and 30th NAL Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Dec},
 note = {The effect of acoustic excitation on the laminar separated flows over an NACA0012 airfoil with the angle of attack 12 deg, at the Reynolds numbers Re = 1 x 10(exp 5), 5 x 10(exp 4) and at the Mach number M = 0.1 investigated numerically. The amplitude of the induced sound pressure is 0.05 percent of the static pressure. Two different effects are observed in the view of the time history of the lift coefficient. One is the small increase of the averaged value and the other is the increase of the oscillation amplitude. These effective frequency ranges are different. The former range depends on the Reynolds number and its mean value is proportional to Re(exp 1/2), while the latter range is independent of Reynolds number. These phenomena are related to the change of vorticity distribution near the laminar boundary layer., 資料番号: AA0045947003, レポート番号: NAL SP-56},
 pages = {7--10},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {弱い音波による層流剥離の数値計算},
 volume = {56},
 year = {2002}
}