NACA 0012 - M 0.7 - 4 º - Residual Problems
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Good night
I'm doing some inviscid simulations over a NACA 0012 at 4º (angle of attack) and M 0,7. What I'm facing is a kind of viscous effect in the NACA surface. The convergence is not good as well. 10^-3 for all the residuals after 5000 iterations. I tried to re-do the mesh but the problem with convergence still there. The setup of the problem is: BC - Pressure Farfield - 67767 Pa - 273,3 K - M=0.7 CFL - 0.5 Second Order upwind - green gauss node based. The mesh has some refinement over the airfoil (0.0002 airfoil -> first layer). From my point of view this kind of effect shouldn't be happening in inviscid simulation. Is this normal for FLUENT ? What should I do to get better convergence ? thanks. |
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