@inproceedings{oai:jaxa.repo.nii.ac.jp:00003847,
 author = {杉浦, 正彦 and 田辺, 安忠 and 菅原, 瑛明 and Sugiura, Masahiko and Tanabe, Yasutada and Sugawara, Hideaki},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32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 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, Helicopter downwash interferes with the ground when a helicopter takes off or lands. By encountering this highly turbulent helicopter wake, two small fixed-wing aircraft were rolled over in the United Kingdom. Japan Aerospace Exploration Agency (JAXA) is investigating the helicopter wake structure in ground effect, especially in taxiing. This year JAXA is going to conduct a helicopter flight test to measure the downwash. Before the flight test, the helicopter downwash is analyzed by CFD in this study to decide the measurement conditions. Firstly, viscous effect on velocity profiles of the downwash is investigated in an isolated rotor analysis. As a result of the governing equations comparison, the flow field in Navier Stokes equations is more realistic than Euler equations. Secondarily, the downwash structures areinvestigated in a rotor-fuselage configuration by changing the taxiing speed. The differences between the downwash structures are clearly observed and the flow field leading to a brownout condition is simulated successfully., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023012, レポート番号: JAXA-SP-14-010},
 pages = {63--68},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {地面効果内のヘリコプタ・ロータによるダウンウォッシュの数値解析},
 volume = {JAXA-SP-14-010},
 year = {2015}
}