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No steady solution for airfoil at high AoA

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Old   January 17, 2020, 16:11
Default No steady solution for airfoil at high AoA
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Hey guys,
I am trying to simulate a NACA 0015 airfoil at high AoA (about 16 degrees)
I am getting oscillating cl and cd values when I run a steady simulation.
Upon switching to an unsteady simulation, for very small time steps( of the order 1e-5) the cl and cd values become constant, but are incorrect. When I increase the timestep ( to about 1s or 2s) the oscillating behavior of cl and cd plots returns.
How do I get convergence?

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airfoil 2d, convergance, fluent

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