@inproceedings{oai:jaxa.repo.nii.ac.jp:00036954,
 author = {浅井, 雅人 and 妹尾, 貴文 and Asai, Masahito and Seno, Takafumi},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Sep},
 note = {28-29 Sep. 1995 (17th). 28-29 Mar. 1996 (18th), 28-29 Sep. 1995 (17th). 28-29 Mar. 1996 (18th), 本研究では、音響外乱に対する翼型周りの流れの応答を、中・高迎角、翼弦長レイノルズ数R(sub c)=2.3×10(exp 4)で、NACA0012翼型について実験的に調べた。中程度の迎角α=10度において、流れは広い周波数範囲にわたり、音響外乱への高い受容性を示し、励起渦が下流側後流を支配した。一方、失速迎角α=16度では、鈍体後流の場合と同様に絶対不安定性の特徴の出現を暗示するように、周期的に近い渦構造が励起のない後流中に出現した。この場合、音響外乱は自然放出周波数およびその周辺以外では後流構造を制御することができなかった。, In the present study, the response of the flow around the airfoil to acoustic forcing examined experimentally for NACA0012 airfoil at moderate and high angles of attack, at a chord-Reynolds number R(sub c) = 2.3 x 10(exp 4). At the moderate angle of attack alpha = 10 deg, the flow is highly receptive to acoustic forcings over a wide range of frequencies, and the excited vortices can govern the downstream wake. At the stall angle alpha = 16 deg, on the other hand, the nearly periodic vortical structures appear in the wake without the forcing, suggesting the appearance of the nature of absolute instability not unlike that of bluff-body wakes. In this case, the acoustic forcing can not control the wake structure except at and around the natural shedding frequency., 資料番号: AA0000867023, レポート番号: NAL SP-33},
 pages = {105--109},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {翼まわりの流れの外乱に対する応答},
 volume = {33},
 year = {1996}
}