ホバリング・ロータに及ぼす翼端形状の影響

Material type: 文書・図像類

Author: 青山, 剛史ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-11

Material Format: Digital

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Note (General)：: A calculation method is developed to analyze the flow around a helicopter blade in hover. Aerodynamic loads generated by a blade are calculated by sol...

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Material Type: 文書・図像類
Title: ホバリング・ロータに及ぼす翼端形状の影響
Author/Editor: 青山, 剛史
河内, 啓二
齊藤, 茂
Aoyama, Takashi
Kawachi, Keiji
Saito, Shigeru
Author Heading: 青山, 剛史
河内, 啓二
齊藤, 茂
Aoyama, Takashi
Kawachi, Keiji
Saito, Shigeru
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-11
Publication Date (W3CDTF): 1989-11
Alternative Title: Effects of Blade Tip Planforms on Rotor Performance in Hover
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: 249-254
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): A calculation method is developed to analyze the flow around a helicopter blade in hover. Aerodynamic loads generated by a blade are calculated by solving the three-dimensional Euler equations in a rotating coordinate system on body-conforming curvilinear grids around a blade. These equations are solved by employing Beam-Warming scheme and TVD scheme is used in order to capture the accurate shock wave. The local induced velocity generated by the rotor-wake is taken into the calculation by subtracting the equivalent angle of attack along the blade from the geometrical one. This equivalent angle of attack is calculated by using prescribed-wake vortex theory. The ability of the present method is verified in comparison with the results of the experiment and the analytical method. In addition, the effects of the planforms of a blade tip on the performance of a helicopter rotor and on the flow around a blade in hover are analyzed. The comparison among swept-back, tapered and swept-back tapered tips is presented. As a result,one tip planform, which has sweep-back angle and inverse-taper, is found to improve the performance of the rotor.
資料番号: NALSP0010042
レポート番号: NAL SP-10
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43371&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43371&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