National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory SP-10
巻
10
ページ
99 - 104
発行年
1989-11
抄録（英）
A numerical procedure to analyze a flowfield through or around a scramjet engine inlet is proposed. The 3-dimensional full Navier-Stokes equations in the generalized curvilinear coordinate system are solved by a time-marching method. The total variation diminishing scheme is applied for spatial discretizations of the convective terms of the equations and the implicit approximate factorization method using diagonalization for simplified inversion work is applied for the time integration. To treat boundary conditions (wall, symmetry etc. ) accurately, all boundaries are mapped onto faces of rectangular parallelepipeds. A computational mesh space is made by connecting them. To show capability of this numerical procedure, numerical simulations of flow are carried out about three inlets with various sweep angles and a common V-shaped thick cowl, which are used in experiments by Kanda et al. The computational results and comparisons with their experiments are presented.
スクラムジェットに関する流れ計算
nalsp0010017.pdf
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