@inproceedings{oai:jaxa.repo.nii.ac.jp:00004717,
 author = {寺島, 洋史 and 河合, 宗司 and 山西, 伸宏 and Terashima, Hiroshi and Kawai, Soshi and Yamanishi, Nobuhiro},
 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, A 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967010, 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 = {高解像度コンパクト差分法を用いた超臨界圧極低温流体の乱流混合解析に向けて},
 volume = {JAXA-SP-10-012},
 year = {2011}
}