大迎角翼型回りの遷音速流の数値解析

Material type: 文書・図像類

Author: 信太, 良文ほか

Publisher: 航空宇宙技術研究所

Publication date: 1987-11

Material Format: Digital

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Note (General)：: Transonic flow around an NACA0012 airfoil at high angle of attack is simulated by solving the two-dimensional Navier-Stokes equations. The block penta...

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Material Type: 文書・図像類
Title: 大迎角翼型回りの遷音速流の数値解析
Author/Editor: 信太, 良文
桑原, 邦郎
Shida, Yoshifumi
Kuwahara, Kunio
Author Heading: 信太, 良文
桑原, 邦郎
Shida, Yoshifumi
Kuwahara, Kunio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1987-11
Publication Date (W3CDTF): 1987-11
Alternative Title: Computation of Flow around NACA0012 Airfoil at High Angle of Attack
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-8
No. or year of volume/issue: 8
Volume: 8
Pages: 73-80
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): Transonic flow around an NACA0012 airfoil at high angle of attack is simulated by solving the two-dimensional Navier-Stokes equations. The block pentadiagonal matrix scheme is employed. Periodic phenomena of shock-wave vortex interaction are observed. For comparison, computation of subsonic flow has been done. Small vortices are observed between the leading edge and the center of the chord.
資料番号: NALSP0008010
レポート番号: NAL SP-8
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43263&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43263&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