Leading edge noise reductions caused by serrations have been shown to be sensitive to the length scales of vortical disturbances. In order to improve the understanding of wavy leading edge airfoils as a noise reduction technology, this paper examines the effects of anisotropy on turbulence-airfoil interaction noise by means of computational aeroacoutic simulations. A synthetic turbulence method is used to generate fully three-dimensional, divergence-free, homogeneous anisotropic turbulence, which is injected in a linearized Euler equation solver to model the noise generation. Moderate variations in turbulence length scales, which are representative of the anisotropy in aero-engine fan wakes, are tested for a NACA 0012 airfoil with a wavy leading edge. This work focuses on the noise sources in the near-field by examining the distortion of the turbulent structures and velocity spectra in the vicinity of the noise sources, the unsteady pressure and its spectral density on the airfoil surface, the magnitude-squared coherence between velocity and pressure fluctuations on the noise sources, and the correlation between noise sources along the span for various degrees of anisotropy. Numerical results show that small variations in the turbulence length scales can produce significant changes in the spectral content of the noise sources at the peak and root regions. The loudest noise source is always located in the root region for the cases examined and this source is mainly affected by the transverse velocity fluctuations. To reduce the correlation between noise sources in the peak and root regions, the ratio between the chordwise length scale and the amplitude of the serrations, and the ratio between the spanwise length scale and the wavelength of the leading edge should satisfy lx/(2hw) < 1 and lz/λw ≤ 0.5, respectively.Recent experimental, numerical, and analytical studies 6,8,14,15 highlighted the importance of the length scales of the vortical disturbances or turbulence as a key parameter in the noise reduction of wavy leading edge airfoils. However, the majority of previous works were based on the flat plate assumption 8, 16 and used simplified representations for the turbulence, such as harmonic gusts 14 or isotropic turbulence. 8 Unlike previous works that focused on flat plates and isotropic turbulence, the present work studies the noise generation mechanisms of an airfoil with wavy leading edge in the presence of anisotropic turbulence. Although the effects of anisotropic turbulence have been shown to be limited in airfoils with straight leading edge, 17 wavy leading edge airfoils are expected to be more sensitive to anisotropic turbulence due to additional three-dimensional mechanisms caused by the amplitude and wavelength of the leading edge serrations. In this work, Computational AeroAcoustic (CAA) simulations are performed by means of a synthetic turbulence method to generate fully three-dimensional anisotropic turbulence and a linearized Euler equation (LEE) solver for the noise generation. The following top...