@inproceedings{oai:jaxa.repo.nii.ac.jp:00003645,
 author = {新井, 翔 and 金崎, 雅博 and 牧野, 好和 and Arai, Sho and Kanazaki, Masahiro and Makino, Yoshikazu},
 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 multi-disciplinary design is an important technique for the efficient design of the supersonic transport (SST), because the designer of SST has to consider the aerodynamics, the structure, and the sonic-boom reduction. High-fidelity flow solver is desirable to solve aerodynamic performance and the sonic boom intensity, however, the employment of the hi-fidelity flow solver is desirable to solve aerodynamic performance and the sonic boom intensity, however, the employment of the hi-fidelity flow solver is time consuming for the preliminary design. In addition, engine nacelle integration should change the optimality of the airframe in view of the aerodynamics and the sonic boom. Thus, it is ideal that engine nacelle integration and the airframe design are considered, simultaneously. In this study, the expanded multi-fidelity design technique is proposed and investigates the difference among the solution. Here, two fidelities are considered: one is the solver fidelity. That is the flow solver whose governing equation is the full-potential equation and the Euler equation. The other is the geometrical fidelity. That is the simple geometry which only has the fuselage, the wing, the stabilizer and the vertical tail and the complex geometry of integrated the engine nacelle. The final goal of this study is to design under consideration of the design knowledge from these fidelities, seamlessly. To evaluate the result estimated by different fidelities, the Kriging model is used. To visualize the knowledge regarding differences Kriging model based analysis of variance (ANOVA) is also employed. Through these investigations, the similar trend can be observed in view of the aerodynamic performance comparing two solvers. On the other hand, geometries which show low sonic boom by the low fidelity solver do not always show low sonic boom in the high-fidelity solver. It suggests that the design knowledge discovery using initial samples is important before the correction of the optimum designs. Comparing with and without engine nacelle configuration evaluated by the high fidelity solver, it is found that the lift is reduced on the inboard wing of the airframe with integrated the engine nacelle. As this result, the cruise angle of attack is different from the airframe without engine nacelle. In addition, pressure centers are different between the airframe with and without engine nacelles, while the pressure center should be agreed with the gravity of the center. This disagreement should be estimated through the geometrical multi-fidelity design process., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005020, レポート番号: JAXA-SP-15-013},
 pages = {133--137},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Multi-fidelity評価を応用した超音速機エンジン統合設計},
 volume = {JAXA-SP-15-013},
 year = {2016}
}