首页> 美国政府科技报告 >Investigation of the aerodynamic environment for an advanced lightweight rotor in forward flight. Volume 2: Laser velocimeter inflow data, advance ratio of 0.37, thrust coefficient of 0.0064 and hover tip speed of 710 feet/second
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Investigation of the aerodynamic environment for an advanced lightweight rotor in forward flight. Volume 2: Laser velocimeter inflow data, advance ratio of 0.37, thrust coefficient of 0.0064 and hover tip speed of 710 feet/second

机译:先进轻型转子在前飞中的气动环境研究。第2卷:激光测速仪流入数据,提前比为0.37,推力系数为0.0064,悬停尖端速度为710英尺/秒

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摘要

An Advanced Lightweight Rotor (ALR) model was tested in high-speed forward flight, mu = 0.37, at the 14- by 22-Foot Subsonic Tunnel at LaRC. A two-component laser velocimeter was used to obtain azimuthally dependent velocities in the inflow region and in the wake of the rotor. Data are presented without analysis.

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