@inproceedings{oai:jaxa.repo.nii.ac.jp:00004407,
 author = {雷, 忠 and Lei, Zhong},
 book = {宇宙航空研究開発機構特別資料: 第43回流体力学講演会: 航空宇宙数値シミュレーション技術シンポジウム2011論文集, JAXA Special Publication: Proceedings of 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011},
 month = {Mar},
 note = {第43回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京, 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8,  2011. Waseda University, International Conference Center), Tokyo Japan, An optimization design methodology for multi-segmented flaps of a supersonic wing has been developed to improve aerodynamic perfomance at taking-off and landing conditions. The geometric shape and computational mesh modification was conducted automatically by a newly-developed tool. Flow field around the configuration was simulated and aerodynamic forces were calculated by solving the Reynolds-averaged Navier-Stokes equations with MPI parallel programming. In the design space, a response surface method was applied to approximately estimate aerodynamic force and largely reduce the number of sampling cases needed. It was confirmed that aerodynamic performane was improved by the optimization design, and the design method was highly efficient to reduce design cost., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065207035, レポート番号: JAXA-SP-11-015},
 pages = {201--207},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {CFDを用いた超音速機多分割前縁フラップ舵角の最適化設計},
 volume = {JAXA-SP-11-015},
 year = {2012}
}