@inproceedings{oai:jaxa.repo.nii.ac.jp:00005748,
 author = {山口, 隼人 and 中村, 佳朗 and Yamaguchi, Hayato and Nakamura, Yoshiaki},
 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 Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京 日本, SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan, Sonic boom is one of the environmental problems produced by aircraft, and reduction in its peak pressure is a significant subject associated with the development of SuperSonic Transport (SST). Recently various low boom configurations are being suggested. In the present study, a Genetic Algorithm (GA) has been applied to aerodynamic shape optimization of an axisymmetric nose (forebody) geometry. The peak overpressure of sonic boom is obtained from an extrapolation of the nearfield pressure signatures with the waveform parameter method. The drag of designed object is calculated based on the pressure distribution along the body surface, which is obtained by solving the Euler equations. In order to reduce the number of function evaluations by CFD (Computational Fluid Dynamics) up to the global optimal solution, a method by the use of approximated functions is proposed., 資料番号: AA0063609017, レポート番号: JAXA-SP-06-029E},
 pages = {128--131},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Optimization of nose shape for reduction of sonic boom},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}