非定常運動をする二次元翼まわりの流れの離散渦法による計算

Material type: 文書・図像類

Author: 麻生, 茂ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-11

Material Format: Digital

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Note (General)：: Separated flows around a wing section at unsteady motion are simulated numerically by a discrete vortex method combined with a panel method. The poten...

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Material Type: 文書・図像類
Title: 非定常運動をする二次元翼まわりの流れの離散渦法による計算
Author/Editor: 麻生, 茂
二ツ寺, 直樹
藤本, 淳
林, 正徳
Aso, Shigeru
Futatsudera, Naoki
Fujimoto, Atsushi
Hayashi, Masanori
Author Heading: 麻生, 茂
二ツ寺, 直樹
藤本, 淳
林, 正徳
Aso, Shigeru
Futatsudera, Naoki
Fujimoto, Atsushi
Hayashi, Masanori
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-11
Publication Date (W3CDTF): 1989-11
Alternative Title: Numerical Calculation of Separated Flows Around a Wing Section at Unsteady Motion by a Discrete Vortex Method
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-10
No. or year of volume/issue: 10
Volume: 10
Pages: 27-32
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): Separated flows around a wing section at unsteady motion are simulated numerically by a discrete vortex method combined with a panel method. The potential flows around wing sections is expressed by vortex sheets and separated shear layers are expressed by discrete vortices. In the calculation a separation point is determined by solving boundary layer equation. The strength of shed vortex is estimated using local velocity near separation point. Also modification for the estimation of pressure coefficients around wing section are proposed. The estimated pressure distributions show good agreements with experimental results. At first calculations are carried out for a wing section at fixed angle of attack. The results show excellent agreements with experiments. Secondly separated flows around pitching airfoils are simulated. A histerisis of lift of airfoil at dynamic stall is obtained in the calculation. Those results suggest that the present method is quite useful to simulate separated flows around wing section both at steady and unsteady motions.
資料番号: NALSP0010005
レポート番号: NAL SP-10
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43334&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43334&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