@inproceedings{oai:jaxa.repo.nii.ac.jp:00005471,
 author = {高木, 正平 and 小西, 康郁 and Takagi, Shohei and Konishi, Yasufumi},
 book = {宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集（第41回・第42回）, JAXA Special Publication: Proceedings of the 41st and 42nd JAXA Workshops on Investigation and Control of Boundar-Layer Transition},
 month = {Feb},
 note = {第41回「境界層遷移の解明と制御」研究会（2007年10月4日-10月5日）, The trailing-edge noise from 2-Dimensional airfoil is experimentally investigated to reveal the mechanism of the frequency selection. The splitter plate is placed at the trailing-edge of the airfoil to produce the no sound emitted condition. At this condition, the instability wave with broad band spectrum which central frequency almost coincides the tonal noise frequency is clearly observed on the pressure side. The artificial acoustic disturbances which are the feedback of the instability wave on the airfoil are introduced at no sound emitted condition, and it is observed that the broad-band spectrum become discrete soon after the feedback is excited. These results confirmed that the trailing-edge noise is the consequence of the acoustic feedback loop between a vortex shedding at the trailing edge and an instability wave on the pressure side of the airfoil., 形態: カラー図版あり, 資料番号: AA0064237013, レポート番号: JAXA-SP-08-006},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {二次元翼後縁騒音の周波数選択機構に関する実験},
 volume = {JAXA-SP-08-006},
 year = {2009}
}