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Experimental Investigation and Fundamental Understanding of a Full-Scale Slowed Rotor at High Advance Ratios

机译:高进给比的全尺寸减速转子的实验研究和基本理解

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This paper describes and analyzes the measurements from a full-scale, slowed revolutions per minute (rpm), UH-60A rotor tested at the National Full-Scale Aerodynamics Complex 40-by 80-ft wind tunnel up to an advance ratio of 1.0. A comprehensive set of measurements that includes performance, blade loads, hub loads, and pressures/airloads makes this data set unique. The measurements reveal new and rich aeromechanical phenomena that are unique to this exotic regime. These include reverse chord dynamic stall, retreating side impulse in torsion load, large inboard-outboard elastic twist differential, diminishing rotor forces and yet a dramatic buildup of blade loads, and high blade loads and yet benign levels of vibratory hub loads. The objective of this research is the fundamental understanding of these unique aeromechanical phenomena. The intent is to provide useful knowledge for the design of high-speed, high-efficiency, slowed rpm rotors of the future and a database for validation of advanced analyses.
机译:本文描述并分析了在国家全尺寸空气动力学综合大楼40 x 80英尺风洞中测试的UH-60A转子的满刻度,慢速每分钟(rpm)的测量结果,其前进比为1.0。包括性能,叶片负载,轮毂负载和压力/空气负载在内的全面测量值使该数据集变得独一无二。测量结果揭示了这种异国风情独特的新颖而丰富的航空机械现象。这些措施包括反弦动态失速,扭转载荷的后退侧向脉冲,较大的舷内外弹性扭转差,减小的转子力以及巨大的叶片载荷累积,较高的叶片载荷和良好的振动轮毂载荷水平。这项研究的目的是对这些独特的航空机械现象的基本了解。目的是为将来的高速,高效,慢转速转子的设计提供有用的知识,并为高级分析的验证提供数据库。

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