@inproceedings{oai:jaxa.repo.nii.ac.jp:00005766,
 author = {牧野, 好和 and 岩宮, 敏幸 and Lei, Zhong and Makino, Yoshikazu and Iwamiya, Toshiyuki and Lei, Zhong},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)},
 month = {Mar},
 note = {SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan, The numerical simulation of a Mach 2.0 scaled supersonic experimental airplane is conducted with the consideration of the integration between airframe and engine nacelles. A three-dimensional Euler CFD (Computational Fluid Dynamics) code with an overset-grids technique is adopted for solving the flow-field around a complex airplane configuration. The calculated pressure distributions are compared with wind tunnel test data and show good agreement with them. The aerodynamic design tool which combines the CFD code with an optimization technique for drag minimization is developed. At first, it is applied to an axisymmetrical body in order to validate this design tool. The result shows that the optimized body geometry agrees well with the Sears-Haack body. Next, it is applied to two bodies under a wing-body configuration. The pressure drag of the optimized configurations is about nine percent lower than that of the Sears-Haack body maintaining their final volumes., 資料番号: AA0063609035, レポート番号: JAXA-SP-06-029E},
 pages = {310--315},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Aerodynamic nacelle shape optimization for NAL's experimental airplane},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}