Aerodynamic/Acoustic Analysis for Main Rotor and Tail Rotor of Helicopter
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概要
- 論文の詳細を見る
A simulation method for full helicopter configuration is constructed by combining an unsteady Euler code and an aero-acoustic code based on the Ffowcs-Williams and Hawkings formulation. The flow field and helicopter noise are calculated using a moving overlapped grid system, and the mutual effect of main rotor and tail rotor are studied for the helicopter in hover or forward flight. In the hovering flight calculation, the tip vortex of the tail rotor is dragged by the induced flow of the main rotor, and the detailed phenomena of the flow pattern are captured well. In the forward-flight calculation, noises from the main rotor and tail rotor are predicted to show tail rotor noise for both self noise and the interaction noise with the main-rotor wake. Comparison of noise magnitude shows the relative importance of tail rotor noise according to flight conditions.
- 社団法人 日本航空宇宙学会の論文
- 2008-05-04
著者
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SAITO Shigeru
Japan Aerospace Exploration Agency
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Aoyama Takashi
Japan Aerospace Exploration Agency
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YANG Choongmo
Japan Aerospace Exploration Agency (JAXA)
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Yang Choongmo
Japan Aerospace Exploration Agency
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Aoyama T
Japan Aerospace Exploration Agency
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KONDO Natsuki
Japan Aerospace Exploration Agency
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Saito S
Japan Aerospace Exploration Agency
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