Boundary Conditions for a standard Airfoil Optimisation Analysis
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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