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規格・テクニカルリポート類

ベクトル計算機に適したオイラー方程式の数値計算法

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ベクトル計算機に適したオイラー方程式の数値計算法

Material type
規格・テクニカルリポート類
Author
森西, 晃嗣ほか
Publisher
航空宇宙技術研究所
Publication date
1985-11
Material Format
Digital
Capacity, size, etc.
-
NDC
-
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Notes on use

Note (General):

出版タイプ: NAAn efficient numerical method has been devised for solving the Euler equations. The method is based on a combination of the central finite di...

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Digital

Material Type
規格・テクニカルリポート類
Author/Editor
森西, 晃嗣
里深, 信行
西田, 秀利
Morinishi, Koji
Satofuka, Nobuyuki
Nishida, Hidetoshi
Publication, Distribution, etc.
Publication Date
1985-11
Publication Date (W3CDTF)
1985-11
Alternative Title
An Easily Vectorizable Numerical Solution of the Euler Equations
Periodical title
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-5
No. or year of volume/issue
5
Volume
5
Pages
89-96
ISSN (Periodical Title)
ISSN : 0289-260X
Text Language Code
jpn
Target Audience
一般
Note (General)
出版タイプ: NA
An efficient numerical method has been devised for solving the Euler equations. The method is based on a combination of the central finite difference approximation to the space variables with the rational Runge-Kutta time integration scheme. To improve the rate of convergence to the steady state solution, residual averaging and a multi-grid technique are incorporated into the basic scheme. The algorithm is very simple to program, easily vectorizable without any additional requirement such as extra memory, and easy to extend to multi-dimensional problems. A series of numerical experiments using the present method has been carried out on the quasi-one-dimensional nozzle flow problem with shock and two dimensional transonic flows over an airfoil. With the implicit residual averaging, the present method is stable until the Courant number reaches about 50. The convergence rate does not monotonously improve as the Courant number is increased. The maximum efficiency for a steady state solution is achieved with a local Courant number of approximately 5. Numerical results for two dimensional transonic flow past airfoils indicate that the efficiency of the present method is just as good as that of the Beam Warming scheme.
資料番号: NALSP0005012
レポート番号: NAL SP-5
Data Provider (Database)
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)
Original Data Provider (Database)
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