@inproceedings{oai:jaxa.repo.nii.ac.jp:00004916,
 author = {真鍋, 圭司 and 西尾, 正富 and Manabe, Keiji and Nishio, Masatomi},
 book = {宇宙航空研究開発機構特別資料: 第41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2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, The hypersonic -flow including shock wave problems are usually analyzed by solving compressible flow equations written by conservative form. In this study, shock wave analysis is carried out by solving non-conservative form of governing equations by Finite Element Method (FEM). First, it is shown that the non-conservative form of 1-dimensional Burgers equation can be properly solved by using upwind scheme of Finite difference method (FDM). This FDM formulation for 1-dimensional non-conservative Burgers equation can be obtained from FEM by using 1-dimensional linear shape function and Upwind Petrov-Galerkin (SUPG) method. Consequently the same computational results of FDM and FEM for 1-dimensional Burgers equation is obtained. Second, compressible Navier-Stokes equations are changed to the non-conservative form. It is important for analyzing shock wave to consider artificial viscosity term, therefore, the non-conservative formulation is conducted for the equation including artificial viscosity term. The detail of the non-conservative formulations of governing equations are shown. This type of equations are introduced to the program of FEM, and the 2-dimensional axisymmetric problem is calculated. The calculation result of shock wave around the Re-entry capsule under the condition of Mach 10 are shown, and the good agreement with experimental result is obtained. It is concluded that non-conservative form of governing equations of compressible fluid can also analyze the shock wave by considering the artificial viscosity term., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672018, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {非保存形のFEM定式による衝撃波解析},
 volume = {JAXA-SP-09-011},
 year = {2010}
}