@inproceedings{oai:jaxa.repo.nii.ac.jp:00004139,
 author = {佐々木, 岳 and 立川, 智章 and 野々村, 拓 and 米本, 浩一 and 大山, 聖 and 松本, 剛明 and 鳴海, 智博 and Sasaki, Gaku and Tatsukawa, Tomoaki and Nonomura, Taku and Yonemoto, Koichi and Oyama, Akira and Matsumoto, Takaaki and Narumi, Tomohiro},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication},
 month = {Nov},
 note = {5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan, The airfoils of Mars exploration aircraft are designed by genetic algorithm and evaluated by computational fluid dynamics. The objectives of optimization are maximization of lift coefficient and minimization of drag coefficient at the angle of attack of 3 degrees. Reynolds number is carefully set to 2.3×10(exp 4), which is the cruising condition of the aircraft. The present computation is utilized supercomputers FX-1 in Institute of Space and Aeronautical Science (ISAS) / Japan Aerospace Exploration Agency (JAXA). The results show that two types of airfoil excel in aerodynamic performance. One airfoil with two large cambers which generate separation bubbles at upper surface has large lift coefficient. The other one with a strong camber in the front of under surface has small drag coefficient and fairy large lift coefficient. Most airfoils on Pareto front have thin thickness under 10% of cord. The present optimization indicates the first step of multi-objective design optimization for practical airfoil design for Mars exploration aircraft, 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062070031, レポート番号: JAXA-SP-13-001E},
 pages = {361--365},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Multi-objective Optimization of Airfoil of Mars Exploration Aircraft using Evolutionary Algorithm},
 volume = {JAXA-SP-13-001E},
 year = {2013}
}