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Other TitleAn Experimental Study of the Rotor/Fuselage Interaction
Author(jpn)田辺, 安忠; 齊藤, 茂; 小曳, 昇; 室田, 勝一; 林, 恭平; 平岡, 克己; 菅原, 瑛明
Author(eng)Tanabe, Yasutada; Saito, Shigeru; Kobiki, Noboru; Murota, Katsuichi; Hayashi, Kyohei; Hiraoka, Katsumi; Sugawara, Hideaki
Author Affiliation(jpn)宇宙航空研究開発機構航空プログラムグループ運航・安全技術チーム; 宇宙航空研究開発機構航空プログラムグループ運航・安全技術チーム; 宇宙航空研究開発機構航空プログラムグループ運航・安全技術チーム; 宇宙航空研究開発機構研究開発本部風洞技術開発センター; 東海大学; 東海大学; 菱友システムズ
Author Affiliation(eng)Operation and Safety Technology Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Operation and Safety Technology Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Operation and Safety Technology Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Wind Tunnel Technology Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Tokai University; Tokai University; Ryoyu Systems
Issue Date2010-08-31
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication titleJAXA reseach and development report
Publication date2010-08-31
AbstractThis paper presents the results of a series of wind tunnel tests on aerodynamic interaction between the rotor and the fuselage. A model rotor test stand JMRTS (JAXA Multi-purpose Rotor Test System) has been used to obtain time-averaged and ensemble-averaged data such as pressure on the blades and fuselage, rotor forces and moments. The blade motions were also calibrated in terms of the collective pitch, flapping and lead-lag angles under both hovering and forward flight conditions. The fuselage of JMRTS is designed after a typical helicopter shape. In the hover cases, it was confirmed that when the rotor thrust was increased, pressure fluctuations on the fuselage increased in amplitude, with the downwash intensified. Moreover, it was spotted in the forward flight cases that time-average pressure distribution measured along a crossline of the fuselage is so asymmetric that the pressure on the retreating side is lower than that on the advancing side. Furthermore, the authors underpinned that the average pressure measured on the fuselage was expressly subject to the rotor downwash when the advance ratio was less than 0.1, while it appeared less affected when the advance ratio was more than 0.1. Consequently, an experimental database, which shall be disclosed to the public for validating CFD codes, was successfully established.
本研究はロータ試験装置として宇宙航空研究開発機構(JAXA)が所有する多目的ロータ試験装置(JAXA Multi-purpose Rotor Test System)にヘリコプタの代表的な形をした胴体模型を設置し、ホバリングから前進飛行まで、さまざまな試験条件でロータと胴体の空力干渉についての試験を行った。基本空カデータと共に、ブレードと胴体表面の平均圧力分布及び圧力変動、ブレードの運動データを取得した。ホバリング試験では、推力の増加とともにダウンウオッシュによる胴体上の圧力変動も大きくなることが確認できた。前進飛行試験では、胴体クロスライン上の平均圧力は非対称であり、ブレード後退側で圧力が負圧になることが確認できた。また、前進mu=0.1以下ではダウンウオッシュの影響が顕著であり、mu=0.1以上ではダウンウォッシュの影響がほとんどないことが確認された。本試験より、ロータと胴体の空力干渉を捉えた CFDの検証用のデータが得られた。
DescriptionOriginal contains color illustrations
形態: カラー図版あり
KeywordsHelicopter, Aerodynamics, Wind tunnel testing, Rotor/Fuselage Interaction, JMRTS
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-10-003

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