@inproceedings{oai:jaxa.repo.nii.ac.jp:00003483,
 author = {岸, 祐希 and 北崎, 慎哉 and Ariyarit, Atthaphone and 牧野, 好和 and 金崎, 雅博 and Kishi, Yuki and Kitazaki, Shinya and Ariyarit, Atthaphone and Makino, Yoshikazu and Kanazaki, Masahiro},
 book = {宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34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 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川, 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan, In this research, the supersonic wing design problem for SST with integrated engine intake and nacelle is discussed to obtain design knowledge of the supersonic airfoil in view of wing planform dependency in realistic configuration. Two planforms were considered ― a quadruple tapered wing with a high sweep-back angle and a single tapered wing with a low sweep-back angle. To reduce the computational time, the design problems were solved by a multi-fidelity design method, which is the evolutionary computation based exploration using the hybrid surrogate models based on two different physical fidelity results. The hybrid surrogate model which was combined Kriging model with radial basis function (RBF) makes optimizations more efficiently than Kriging model. To evaluate the aerodynamic performance, the compressive Euler equation and the linearized compressive potential equation were employed as two different fidelity solvers. Through optimum designs, two kinds of design knowledge are obtained. Firstly, in airfoil design, the shape of the forward camber and twisted angle have the largest effect on drag reduction. In case of low sweep-back wing, an airfoil which has small positive camber and small twisted down angle has found to be optimum. On the other hands, In case of low sweep-back wing, an airfoil which has a negative camber at the leading edge or higher twisted down angle compared to low swept-back wing’s one has shown to be optimum. Secondly, the way of aerodynamic interference between wing, engine, and fuselage depends on planforms., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031008, レポート番号: JAXA-SP-16-007},
 pages = {85--90},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {エンジンインテーク統合時における超音速最適翼型の平面形依存性に関する調査},
 volume = {JAXA-SP-16-007},
 year = {2016}
}