Flow Duct
Application ID: 1371
The acoustic field in a model of an axially symmetric lined aero-engine duct, based on modal sound transmission, is analyzed. The source is generated by a single mode excitation at a boundary. Sources and nonreflecting conditions are applied using port boundary conditions. The model analysis is performed in three steps, first computing the background mean flow (compressible irrotational potential flow), then analyzing the propagating modes with a boundary mode analysis, and finally solving the acoustic field in the flow duct with the linearized potential flow equations. Results are presented for situations with and without a background flow and for the cases of hard and lined duct walls.
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