Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010
巻
JAXA-SP-10-012
発行年
2011-02-28
会議概要（会議名, 開催地, 会期, 主催者等）
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)
会議概要（会議名, 開催地, 会期, 主催者等）（英）
42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25, 2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan
抄録（英）
In this study, flow and acoustic fields of a supersonic jet impinging on an inclined flat plate are investigated. Compressible Navier-Stokes equations are solved by a high-order shock capturing scheme with two different computational grids for investigating the effects of resolution of turbulent boundary layer. Total numbers of computational grids are 30 million and 700 million where a 700-million computational grid is designed for resolving turbulent boundary layer. From the near-wall structure, streak-like structures are observed in the case with a 700-million computational grid while such structures are not observed in the case with a 30-milliion computational grid. In spite of the difference in the resolution of turbulent boundary layer, essential flow and acoustic fields do not change for both cases. This indicates that flow and acoustic fields are insensitive to the resolution of turbulent boundary layer.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
斜め平板に衝突する超音速ジェットと発生音響波の超大規模LES解析
64967012.pdf
(1.66MB)
