A new method for determining acoustic-liner admittance in a rectangular duct with grazing flow from experimental data
Willie R. Watson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Technology & Engineering - 16 pages
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acoustic pressure eigenfunction admittance 3W Admittance values determined analytical program axial propagation constant boundary conditions constant mean-flow profile continuity of acoustic-particle coordinate system cross-mode order determine the admittance dimensionless axial propagation duct with grazing eigenfunction F(y elimination is employed equa equation 14 equation 20 exact values expressed f b,b f y,b finite-element discretization first-order mode flows with two-dimensional form P(y,z functions F(y Gaussian elimination Global coordinate gradients grazing flow Grazing-flow admittance grazing-flow impedance tube Grazing-flow impedance-tube test h both set hard-wall duct input into equation K M(b Kx values corresponding Langley Research Center last row line element linear eigenvalue problem lower walls measured data method employed NASA nodes numerical method one-dimensional boundary layer ordinary differential equation Performing Organization Pw,u rectangular duct row and column Runge-Kutta integration technique rw,u SHEAR FLOW solution to equation stant third-order mode tion transverse directions unknown admittance value Unlike existing methods wave number