  This study investigates the flow evolution past a pitching NACA0012 airfoil
undergoing deep dynamic stall using a wall-resolved large eddy simulation
approach. Numerical results are validated against experimental data from Lee
and Gerontakos at Reynolds number Re = 135 000 and a reduced frequency k = 0.1.
A comprehensive analysis of the computational grid span size is presented,
highlighting the critical requirement for a span-to-chord ratio of at least
one. Furthermore, a comparative assessment with state-of-the-art RANS and
hybrid RANS/LES turbulence models is conducted to identify the sources of
potential discrepancies between the numerical simulations and the experimental
data. All the numerical models demonstrate the same behavior and exhibit
similar differences with the experiments.
