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Boundary Conditions for a standard Airfoil Optimisation Analysis

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Old   March 15, 2013, 18:28
Default Boundary Conditions for a standard Airfoil Optimisation Analysis
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I am in the process of setting up a mesh that is to be used for an airfoil optimisation analysis. The problem I am having is during testing of a standard NACA 0012 airfoil, my lift coefficients seem to be fluctuating a bit, and never seem to be quite right. I was just wondering if anyone could spot something I have done wrong with my boundary conditions. I have attached a picture with them to this post.

Any help would be fantastic!

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