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- W2081283364 abstract "In order to develop an accurate prediction method for the acoustic impedance and hence attenuation performance of jet engine liners in flow conditions, it is necessary to understand the detailed flow-acoustic interactions taking place at the liner surface. As a first step, a single cell of a perforate-faced cavity type of liner has been modelled by a rectangular cavity with a rectangular slot mouth set into the wall of the working section of a Mach 0·5 wind tunnel. By using microphones, hot wire anemometry and Laser-Doppler Velocimetry measurements have been made of the acoustically driven flow field in the mouth of the cavity when it is subjected to grazing flow and acoustic excitation in conditions approaching those found in a jet engine liner. (I.e., incident SPL>130 dB, boundary layer turbulence level ≊12%), in order to provide as much information as possible on the sort of pressure and velocity fields to be expected there. The results are discussed in the light of existing theoretical models concerning flow induced impedance changes of cavities. In general it is found that these models are inadequate in explaining phenomena in the real case but that certain features are worthy of further development. In particular the approach taken by Nelson et al. [1,2] in which the measured pressure and velocity fields are modelled as the superposition of those produced separately by the reciprocating potential flow (associated with the acoustic excitation) and the vorticity distribution lends itself most readily to explaining the presented results." @default.
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- W2081283364 date "1985-12-01" @default.
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- W2081283364 title "Jet engine liner impedance: An experimental investigation of cavity neck flow/acoustics in the presence of a Mach 0·5 tangential shear flow" @default.
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- W2081283364 doi "https://doi.org/10.1016/s0022-460x(85)80025-0" @default.
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