@inproceedings{oai:jaxa.repo.nii.ac.jp:00003643,
 author = {菅原, 瑛明 and 田辺, 安忠 and Sugawara, Hideaki and Tanabe, Yasutada},
 book = {宇宙航空研究開発機構特別資料: 第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京, 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan, The aerodynamic performance of a full-scaled helicopter rotor is predicted using a rotorcraft CFD solver, rFlow3D. The prediction accuracy is verified through comparison with the selected wind tunnel test data of a constant thrust while the advance ratio is increased up to 0.4. Trim adjustment is improved by implementing a look-up table for the sectional aerodynamics. The rotor control angles and rotor drag and power between prediction and experiment are found in acceptable agreement. Some differences in the collective and lateral pitch angles are observed due to not including the elastic deformations in the analysis. Detailed comparisons of the sectional airloads are also performed and good correlations are found. The aerodynamic loads in the reversed flow region are also obtained. The influence of the elastic deformation on the prediction accuracy of aerodynamic performance at high advance ratio conditions will be further studied., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005018, レポート番号: JAXA-SP-15-013},
 pages = {121--126},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {ヘリコプタの高速飛行時の空力性能予測},
 volume = {JAXA-SP-15-013},
 year = {2016}
}