@inproceedings{oai:jaxa.repo.nii.ac.jp:00004745,
 author = {村上, 直哉 and 久保田, 弘敏 and Murakami, Naoya and Kubota, Hirotoshi},
 book = {宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, In 2010, the Space Shuttle is supposed to retire because of its aging and high maintenance cost. As a future space transportation system, a reusable space plane is expected. If a space plane is realized in the future, it will fly at hyper- or supersonic speed overland. Therefore, sonic boom will become a big issue for space plane. At first in this study, sonic boom intensity of the Space Shuttle is predicted with waveform parameter method from the wind tunnel test data conducted by NASA. The results suggest that considering the way to reduce sonic boom is also important for future space transportation system. Therefore, reduction of sonic boom intensity of a space plane which flies at hypersonic speed is attempted with Seebass-George-Darden-Rallabhandi method. As a result, the optimized far-field pressure signatures for the space plane might be acceptable for people of 65％ population. Since, the fuselage that has large bluntness is generally known to be effective for the sonic boom reduction, the effects of changing bluntness for the far field pressure signatures are investigated. The results show two promising low sonic boom signatures. One is a signature whose peak pressure value becomes smaller without changing its typical low boom waveform shape. The other is a signature that has N-shape like waveform while keeping a small initial pressure peak. In addition, it is shown that a small change in the near field pressure signatures causes big change in the far field pressure signature, because non-linear effects are large in the hypersonic speed. For future works, to demonstrate these results is necessary by CFD or wind tunnel tests., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967038, レポート番号: JAXA-SP-10-012},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {スペースシャトルおよび宇宙往還機のソニックブーム強度予測と低減化},
 volume = {JAXA-SP-10-012},
 year = {2011}
}