  We simulate the two-dimensional fluid flow around National Advisory Committee
for Aeronautics (NACA) 0012 airfoil using a hybrid lattice Boltzmann method
(HLBM), which combines the standard lattice Boltzmann method with an
unstructured finite-volume formulation. The aim of the study is to assess the
numerical performances and the robustness of the computational method. To this
purpose, after providing a convergence study to estimate the overall accuracy
of the method, we analyze the numerical solution for different values of the
angle of attack at a Reynolds number equal to $10^3$. Subsequently, flow fields
at Reynolds numbers up to $10^4$ are computed for a zero angle of attack
configuration. A grid refinement scheme is applied to the uniformly spaced
component of the overlapping grid system to further enhance the numerical
efficiency of the model. The results demonstrate the capability of the HLBM to
achieve high accuracy near solid curved walls, thus providing a viable
alternative in the realm of off-lattice Boltzmann methods based on body-fitted
mesh.
