@inproceedings{oai:jaxa.repo.nii.ac.jp:00047340,
 author = {菅谷, 圭祐 and 今村, 太郎 and SUGAYA, Keisuke and IMAMURA, Taro},
 book = {宇宙航空研究開発機構特別資料: 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2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {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2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), In this study, the unsteady flow simulation around the 30P30N high-lift airfoil is conducted to investigate the noise prediction capability of the hierarchical Cartesian-grid-based flow solver. To calculate the turbulent boundary layer, the Immersed Boundary method and the wall function are used. The computational grid is refined around the slat and the slat trailing edge to predict the noise from the slat accurately. The number of grid cells is over 100 million. The time-averaged surface pressure coefficient distributions on the airfoil surface agree with the experimental data quantitatively and qualitatively. The Power Spectral Density of the wall pressure obtained by this simulation agrees with the experimental data. Furthermore, the effect of the angle of attack on the slat noise is simulated well., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013019, レポート番号: JAXA-SP-20-008},
 pages = {143--147},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {階層型直交格子と埋め込み境界法を用いた30P30N高揚力装置の非定常流解析},
 volume = {JAXA-SP-20-008},
 year = {2021}
}