並列タイトル等Numerical Simulation of Shcok Wave Emanating from a Square Shock Tube
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-14
一般注記We studied the flowfield behind a shock wave emitted from a square shock tube. Being three-dimensional, it allows to observe various phenomena for axisymmetric flow such as distorted vortex ring structure generated from the shock tube exit, shock wave deformation and a variety of flow structures behind the shock wave. If the generative mechanisms of distorted vortex ring and flows from the shock tube are clear, this also contributes to the technical advancing, regarding the mixture of different chemical species, as, e.g., fuel and an oxidizing agent, etc. In this paper, the shock wave emanating from a square shock tube was studied in numerical simulation and shock tube experiment, as well. In order to simulate these flow fields, a second order upwind TVD finite difference scheme (Harten-Yee type) was used. This TVD scheme, having been used for two-dimensional problems, was extended to three-dimensions and applied to Euler equations. The computational domain of 60 by 60 by 60 grid points covers a quarter of the shock tube cross section. As an initial configuration we took a normal shock wave with Mach number 1.5. The numerical results were compared with data from optical measurements. The double exposure holographic interferometry was used to photograph the emerging shock wave. We were able to obtain good qualitatively agreement between numerical results and experimental ones. The formation of shock wave and the generative mechanism in the unsteady three-dimensional shock tube flow are discussed by detailed analysis of the numerical results, and these flow properties were clarified.
資料番号: NALSP0014032
レポート番号: NAL SP-14
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43465&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ