A model for the prediction of wake‐related sound generation by a single airfoil is presented which assumes that the net force fluctuation on an airfoil can be expressed in terms of the net momentum fluctuation in the near wake of the airfoil. The model predicts a forcing function for sound generation which is related to the spectra of the two‐point velocity correlations in the turbulent region near the airfoil trailing edge. Cross spectra were obtained from correlations of the longitudinal and transverse components of turbulence in the wake of a 36‐in. chord NACA series 63‐009 airfoil in the 7×10 ft tunnel at the NASA Ames Research Center usingx‐probe hot‐wire sensors. Additional data were obtained from a 10‐in. chord airfoil in a free‐jet facility at the University of Washington. Based on results from these tests, a scaling model was developed using the turbulent boundary‐layer thickness as the primary length measure. The model was used to predict the sound radiated from a 2‐in. chord airfoil for which acoustical data is available with good agreement both in level and spectral shape. The single airfoil result is extended to a rotor geometry and comparisons studied for various aerodynamic parameters.Subject Classification:[43]28.65; [43]50.55.