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For analyzing stall, simulation is performed at maximum aileron deflection and at expected cruising speed. Initially, a steady state simulation was run but the plots of residuals, lift & drag had a lot of noise. A transient simulation is also performed, which led to a less oscillating values. Pictures are shown below:
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Something to note is that the result shown in Fig. 5 was an assembly geometry where the aileron and wing were separate bodies. There was some gap between the aileron and the wing. To simplify the meshing/discretization process, a single body CAD was created (used for simulation in fig. 6 and 7)
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There are no large vorticities above the aileron, hence no significant sign of stall.
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