@inproceedings{oai:jaxa.repo.nii.ac.jp:00006640,
 author = {金崎, 雅博 and 藤原, 仁志 and 伊藤, 靖 and 藤田, 健 and 大林, 茂 and 中橋, 和博 and Kanazaki, Masahiro and Fujiwara, Hitoshi and Ito, Yasushi and Fujita, Takeshi and Obayashi, Shigeru and Nakahashi, Kazuhiro},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {In this paper, the numerical simulation method for the supersonic intake performance is proposed. According to the wind tunnel test by NAL, the performance of the supersonic intake integrated to a wing-body was different from the nacelle-only configuration. This result suggested that the intake performance is affected by the wing-body existence. To inspect this difference, the simulations with the nacelle-only configuration and wing-body-nacelle configuration were performed and the calculative results were compared. To obtain higher numerical accuracy of the shock wave, the structured Navier-Stokes code with the low-Reynolds number kappa-epsilon turbulent model were applied to inside the nacelle, while to adapt to the complex geometry of the wing-body-nacelle configuration, the unstructured Euler code was applied to outside the aircraft model. To perform this calculation, the structured-unstructured zonal approach was developed., 資料番号: AA0047427039, レポート番号: JAXA-SP-03-002},
 pages = {220--225},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {構造-非構造接続法によるNALジェット実験機機体統合超音速インテーク性能解析},
 volume = {JAXA-SP-03-002},
 year = {2004}
}