@inproceedings{oai:jaxa.repo.nii.ac.jp:00049144,
 author = {八代, 理聖 and 岸, 祐希 and 金崎, 雅博 and YASHIRO, Risato and KISHI, Yuki and KANAZAKI, Masahiro},
 book = {宇宙航空研究開発機構特別資料: 第54回流体力学講演会/第40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 54th Fluid Dynamics Conference / the 40th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第54回流体力学講演会/第40回航空宇宙数値シミュレーション技術シンポジウム (2022年6月29日-7月1日. いわて県民情報交流センター(アイーナ)), 盛岡市, 岩手, The 54th Fluid Dynamics Conference / the 40th Aerospace Numerical Simulation Symposium (June 29 - July 1, 2022. Iwate Citizen Information Exchange Center (Aiina)), Morioka, Iwate, Japan, In this paper, the equivalent area distribution of a ten-seater supersonic forward-swept wing aircraft with canard was designed to obtain design knowledge toward the leading boom reduction. The equivalent area distribution of the aircraft was calculated by solving the compressible Euler equation, and a feasible target equivalent area distribution was generated based on Darden's method and compared with the equivalent area distribution. To acquire closer lift and geometry to the target, the main wing planform and the position of the main wing along the body axis and the vertical axis were modified, and the low boom performances were evaluated using the extended Burgers equation. The design results suggested that the forward-swept wing configuration with canard can divide the single peak of the leading boom into two peaks; thus, the sonic boom loudness of canard configuration was 2.5 PLdB lower than without-canard configuration., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2230023013, レポート番号: JAXA-SP-22-007},
 pages = {183--195},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {等価断面積設計法を用いた先尾翼前進翼機の低ブーム設計},
 volume = {JAXA-SP-22-007},
 year = {2023}
}