*α* =14<sup>0</sup> ± 5.5**sin**(**ωt**)<sup>0</sup>

Figure 20 illustrates the evolution of the aerodynamic coefficients with oscillation of the AoA around 140 with amplitude of 5.50 and a reduced frequency of 0.026. As the angle ex‐ ceeds 140 , the purely turbulent k-ω SST model was used.

We note that before 17°, the model overestimates the drag coefficient, both for increasing and decreasing AoA. For angles exceeding 17°, the model approaches experimental results. As for the drag coefficient, the model provides better results for the lift coefficient when the angle of attack exceeds 17°. Furthermore, we note that the model underestimates the lift co‐ efficient for both increasing and decreasing angles of attack. Moreover, the predicted lift co‐ efficients are closer to experimental results for AoA less than 13°.

**Figure 20.** Drag and lift coefficients vs. angle of attack for stall modelling
