A scaled landing gear has recently been tested in the NRC 0.9 m 3/4-open jet wind tunnel. It provided experimental data that were used to investigate the capability and methodology of a CFD flow solver to predict adequately the noise generated on the landing gear surfaces and in its wake. Near-field and far-field noise predictions using CFD were carried out. FFTs of the landing gear surfaces for a given frequency were also carried out. Comparison of the results demonstrates that CFD can predict adequately the noise around complex geometries such as landing gears. Nomenclature C p = pressure coefficient dB = decibels f = frequency FFT = fast Fourier transform Hz = hertz k = turbulent kinetic energy SPL = sound pressure level u ' = local perturbation velocity X,Y,Z = axis coordinates in wind tunnel y + = law-of-the-wall coordinate ∆ = cell dimension ε = turbulent dissipation rate
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