This article demonstrates the conception of numerical techniques for simulating the flow around a NACA 0012 airfoil oscillating at its quarter-chord point. These simulations solve the physics of the dynamic stall phenomenon on an oscillating airfoil case. To do so, a two-dimensional framework is used to achieve feasible aerodynamic predictions. The simulations are required to test aerodynamic coefficients, corresponding to PIV (particle imaging velocimetry) images acquired experimentally according to the literature. A qualitative and quantitative agreement is expected between the simulation and the experimental results for both cases.