A New Method of Estimating the Lateral Wall Effect on the Airfoil Incidence due to the Suction at Side Walls

Material type: 文書・図像類

Author: 沢田, 秀夫ほか

Publisher: 航空宇宙技術研究所

Publication date: 1981-08

Material Format: Digital

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Note (General)：: A new method of estimating the lateral wall effect on the airfoil incidence due to the suction at the side walls through porous plates is presented. T...

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Material Type: 文書・図像類
Title: A New Method of Estimating the Lateral Wall Effect on the Airfoil Incidence due to the Suction at Side Walls
Author/Editor: 沢田, 秀夫
榊原, 盛三
佐藤, 衛
神田, 宏
唐沢, 敏夫
SAWADA, Hideo
SAKAKIBARA, Seizo
SATO, Mamoru
KANDA, Hiroshi
KARASAWA, Toshio
Author Heading: 沢田, 秀夫
榊原, 盛三
佐藤, 衛
神田, 宏
唐沢, 敏夫
SAWADA, Hideo
SAKAKIBARA, Seizo
SATO, Mamoru
KANDA, Hiroshi
KARASAWA, Toshio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1981-08
Publication Date (W3CDTF): 1981-08
Alternative Title: 側壁からの吸い込みによる翼型迎角への側壁干渉効果の新しい評価法
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-680
No. or year of volume/issue: 680
Volume: 680
Pages: 18-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): A new method of estimating the lateral wall effect on the airfoil incidence due to the suction at the side walls through porous plates is presented. The normal component of the velocity to the plates must be known on the plates when this method is used. The velocity component is approximated from the pressure difference across the plates by the aid of an experimental equation which states that the normal velocity component to a porous plate induced by the pressure difference across the plate is proportional to the square root of the pressure difference. In this method, the proportional constant number need not be known. An experiment was carried out to ascertain the lateral wall effect due to the suction at the side walls. The pressure in the suction box, one side of which consisted of a porous plate, was set at various values in this experiment. The lift coefficient of an airfoil model changed with the variation of the pressure in the suction box even at the same uniform flow speed and the same incidence. The unique value of the lift coefficient was determined from several such lift coefficients at the same incidence by this method. The corrected lift coefficient curve obtained by this method is very close to one obtained in a test section with fully solid side walls.
資料番号: NALTR0680000
レポート番号: NAL TR-680
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