AF2法による遷音速翼型まわりの流れの数値解析

Material type: 文書・図像類

Author: 里深, 信行ほか

Publisher: 航空宇宙技術研究所

Publication date: 1984-11

Material Format: Digital

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Note (General)：: An approximate factorization scheme has been developed for analyzing transonic flows past an airfoil. In this scheme, upwind differencing is used for ...

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Material Type: 文書・図像類
Title: AF2法による遷音速翼型まわりの流れの数値解析
Author/Editor: 里深, 信行
西田, 秀利
Satofuka, Nobuyuki
Nishida, Hidetoshi
Author Heading: 里深, 信行
西田, 秀利
Satofuka, Nobuyuki
Nishida, Hidetoshi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1984-11
Publication Date (W3CDTF): 1984-11
Alternative Title: Numerical Analysis for Steady Transonic Flows Past an Airfoil Using AF 2 Scheme
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-3
No. or year of volume/issue: 3
Volume: 3
Pages: 193-200
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): An approximate factorization scheme has been developed for analyzing transonic flows past an airfoil. In this scheme, upwind differencing is used for introducing artificial viscosity in the supersonic region and central differencing is used in the subsonic region. The resulting simple two- and three-banded matrices are solved by the relaxation proce-dure. This scheme is fully implicit, and in principle can be combined with the solution-adaptive method. In both sub- and super-critical cases, the computed surface pressure distributions for an NACA0012 airfoil are in good agreement with those obtained by other methods.
資料番号: NALSP0003024
レポート番号: NAL SP-3
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43166&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43166&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
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）
https://irdb.nii.ac.jp
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