@inproceedings{oai:jaxa.repo.nii.ac.jp:00003482,
 author = {上野, 篤史 and 野口, 正芳 and 牧野, 好和 and Ueno, Atsushi and Noguchi, Masayoshi and Makino, Yoshikazu},
 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, The aft-boom shaping for a small supersonic transport is performed and is validated by the wind tunnel test. First, the parametric study of horizontal stabilizer shape using the low-fidelity design tool is conducted in order to fragment the aft boom into two shock waves. Though the nacelle is not modeled in this design, the negative effect of nacelle pressure waves on the aft-boom is considered, and pressure waves caused by the horizontal stabilizer is strengthened to realize the fragmentation. Results show the importance of inverse camber and extended root chord length in order to realize both low-drag and low-boom. Then, wind tunnel test and high-fidelity CFD (FaSTAR) analysis for the designed shape without nacelle are performed. Near-field pressure signatures obtained by wind tunnel test and FaSTAR analysis agree well. Finally, FaSTAR analysis is performed for the designed shape with nacelle and shows that the aft-boom is successfully fragmented into two shock waves even though the coalescence of these two shock waves is advanced by the nacelle expansion wave., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031007, レポート番号: JAXA-SP-16-007},
 pages = {79--84},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {小型超音速旅客機の後端低ブーム設計と風洞試験による検証},
 volume = {JAXA-SP-16-007},
 year = {2016}
}