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Noise of a model high speed counterrotation propeller at simulated takeoff/approach conditions (F7/A7)

机译:模拟起飞/进近条件下的模型高速反向旋转螺旋桨的噪音(F7 / A7)

摘要

A high speed advanced counterrotation propeller, was tested in the NASA-Lewis 9 x 15 foot Anechoic Wind Tunnel at simulated takeoff/approach conditions of 0.2 Mach number. Acoustic measurements were taken with fixed floor microphones, an axially translating microphone probe, and with a polar microphone probe which was fixed to the propeller nacelle and could take both sideline and circumferential acoustic surveys. Aerodynamic measurements were also made to establish the propeller operating conditions. The propeller was run over a range of blade setting angles from 36.4/36.5 to 41.1/39.4 deg, tip speeds from 165 to 259 m/sec, rotor spacings from 1.56 to 3.63 based on forward rotor tip chord to aerodynamic separation, and angles of attack to + or - 16 deg. First order rotor alone tones showed highest directivity levels near the propeller plane, while interaction tone showed high levels throughout sideline directivity, especially toward the propeller rotation axis. Interaction tone levels were sensitive to propeller row spacing while rotor alone tones showed little spacing effect. There is a decreased noise level associated with higher propeller blade numbers for the same overall propeller thrust.
机译:在NASA-Lewis 9 x 15英尺消声风洞中模拟了0.2马赫数的起飞/进近条件下对高速先进的反向旋转螺旋桨进行了测试。声学测量是使用固定的地板麦克风,轴向平移的麦克风探头以及固定在螺旋桨机舱上的极性麦克风探头进行的,可以同时进行边线和周向声学测量。还进行了空气动力学测量以确定螺旋桨的运行条件。螺旋桨在36.4 / 36.5度至41.1 / 39.4度的叶片设定角度范围内运行,叶尖速度从165至259 m / sec,基于前旋翼叶尖弦到空气动力分离的旋翼间距从1.56至3.63,以及攻击+或-16度。一阶旋翼单独的音调在螺旋桨平面附近显示出最高的方向性水平,而相互作用音调在整个副线方向性上都表现出高水平,尤其是在螺旋桨旋转轴方向。交互音调水平对螺旋桨行距很敏感,而单独的旋翼音调显示出很小的间距效应。对于相同的总螺旋桨推力,与较高的螺旋桨叶片数量相关的噪音水平有所降低。

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    Woodward Richard P.;

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  • 年度 1987
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