Institute of Fluid Science, Tohoku University
National Aerospace Laboratory
Tohoku University Graduate School of Engineering
Tohoku University Graduate School of Engineering
Institute of Fluid Science, Tohoku University
Tohoku University Graduate School of Engineering
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
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
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003
巻
JAXA-SP-03-002
ページ
220 - 225
発行年
2004-03-25
抄録（英）
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.
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
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