Impingement of a propeller-slipstream on a leading edge with a flow-permeable insert: A computational aeroacoustic study
Impingement of a propeller-slipstream on a leading edge with a flow-permeable insert: A computational aeroacoustic study
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螺旋桨滑流对带有透流插入件的前缘的冲击:计算气动声学研究
DOI:
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发表时间:
2018
影响因子:
1
通讯作者:
D. Ragni
中科院分区:
文献类型:
--
作者:
F. Avallone;D. Casalino;D. Ragni
This manuscript describes an aeroacoustic computational study on the impingement of a tractor-propeller slipstream on the leading edge of a pylon. Both the flow and acoustic fields are studied for two pylon leading edges: a solid and a flow-permeable one. The computational set-up replicates experiments performed at Delft University of Technology. Computational results are validated against measurements. It is found that the installation of the flow-permeable leading-edge insert generates a thicker boundary layer on the retreating blade side of the pylon. This is caused by an aerodynamic asymmetry induced by the helicoidal motion of the propeller wake, which promotes a flow motion through the cavity from the advancing to the retreating blade side of the pylon. The flow-permeable leading-edge insert mitigates the amplitude of the surface pressure fluctuations only on the pylon-retreating blade side towards the trailing edge, thus reducing structure-borne noise. Furthermore, it causes a reduction of the near-field noise only for receiver angles oriented in the upstream direction at the pylon-retreating blade side. In this range of receiver angles, it is found that the flow-permeable leading-edge insert reduces the amplitude of the tonal peaks for the third and fourth blade passage frequency, but strongly increases the broadband noise for frequencies higher that the seventh blade passage frequency.