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January 17, 2020, 15:11
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No steady solution for airfoil at high AoA
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#1 |
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New Member
Join Date: Sep 2019
Posts: 24
Rep Power: 6  |
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? NonStopEagle |
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| airfoil 2d, convergance, fluent |
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