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仪器网/ 行业应用/ 解决方案/ 悬停状态下小尺度旋翼的近场压力

悬停状态下小尺度旋翼的近场压力

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The pressure field within the near field periphery of a small scale rotor blade is investigated by means of
classical statistical analysis techniques and proper orthogonal decomposition. The signatures are acquired using
a circular arc array of dynamic pressure transducers, centered on the rotor tip at a distance of 1.5 chord
lengths and below the tip path plane. The rotor is set to collective pitch angles ranging from 0. to 12. and
is operated at 35Hz and 25Hz rotor speeds under hover conditions. Each blade from this two bladed rotor
is investigated independently in order to isolate pressure signal differences existing between the blades. The
results show that while the average inter-blade signatures are relatively constant, the variance of the fluctuations
possess noticeably different amplitudes. Given the scale of the rotor, these differences are attributed
to the surface roughness effects. A low-dimensional analysis reveals that the first few most energetic modes
produced by each blade are relatively consistent in shape and so concerns about differences between the signatures
produced by each blade are contracted. Two important features about the near-field signatures are
then revealed. The first is a low frequency, low wave-number type oscillation and is observed in all microphone
signals positioned between the tip path plane and 75. below. The second signature however comprises a high
frequency, high wave-number signature that manifests itself at shallow angles relative to the tip path plane of
the rotor. The latter of these is believed to be the associated with the radiating component of the pressure field
produced by interactions of the rotor blade with the tip-vortex. A low-dimensional reconstruction of the raw
pressure signal illustrates how each of these signatures contribute independently to the original raw signal. 德国LaVision PIV/PLIF粒子成像测速场仪 三维立体PIV
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