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Other TitleA high-resolution scheme for cryogenic turbulent mixing flows under supercritical pressure environments
Author(jpn)寺島, 洋史; 河合, 宗司; 山西, 伸宏
Author(eng)Terashima, Hiroshi; Kawai, Soshi; Yamanishi, Nobuhiro
Author Affiliation(jpn)宇宙航空研究開発機構; 宇宙航空研究開発機構
Author Affiliation(eng)Japan Aerospace Exploration Agency (JAXA); Stanford University; Japan Aerospace Exploration Agency (JAXA)
Issue Date2011-02-28
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication titleJAXA special publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010
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
Publication date2011-02-28
AbstractA high-resolution methodology using a compact differencing scheme is introduced in the aim of simulating cryogenic turbulent mixing flows under supercritical pressure environments. The present method takes a strategy to add non-linear localized artificial diffusivity to capture different types of discontinuities such as shock waves or material interfaces, while using a compact difference scheme. One-dimensional advection and modified Shu-Osher problems in supercritical flows are proposed in this study to assess the performance of the present method, in addition to an existing shock tube problem. Results for the advection problem show that the present method can be applied successfully to supercritical flows, including a trans-critical state, without any significant spurious oscillations, if initial startup errors are properly avoided. A localized artificial diffusivity, especially artificial thermal conductivity for temperature gradients, can effectively work on reducing numerical wiggles produced due to high density/temperature gradients. The modified Shu-Osher problem demonstrates the superiority of the present method in resolving high-frequency waves behind the shock wave even in a supercritical pressure condition, relative to a conventional low-order upwind-biased scheme. Results for a two-dimensional cryogenic plane jet in a supercritical pressure condition also demonstrate the capability of the present method for simulating the unsteady jet flow structures and the superiority for resolving the fluctuations with reasonable grid resolutions.
DescriptionOriginal contains color illustrations
Meeting Information: 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25, 2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan
形態: カラー図版あり
会議情報: 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)
Document TypeConference Paper
JAXA Category特別資料
Report NoJAXA-SP-10-012

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