Comparative analyses reveal trailing edge noise characteristics in NACA0016 airfoil, indicating implications for propeller and rotor noise assessments.
In this study, we investigated the trailing-edge (TE) noise of a turbulent boundary layer (TBL) over a symmetric airfoil by examining the wall pressure spectra predicted by four different models, while systematically identifying and comparing key parameters and constants. We computed the TBL-TE noise-associated acoustic power spectral density using Amiet’s theory, which can be applied to propeller and rotor noise analysis. Numerical predictions of the one-third octave-band noise spectra for a NACA0012 airfoil exhibited excellent agreement with experimental data, and the far-field directivity pattern exhibited distinct side-lobe behavior at high frequencies. Based on these results, we conducted comparative analyses using the NACA0016 airfoil (commonly employed as a reference section in studies of vertical-axis wind turbine blades, horizontal control surfaces of underwater vehicles, and biomimetic airfoils) to assess far-field noise spectra, directivity, and noise scaling with flow velocity against established theoretical predictions.
No takes yet. Share an insight, caveat, or question.
Ryu et al. (2026) studied this question.
Synapse has enriched 5 closely related papers on similar clinical questions. Consider them for comparative context: