cd and cl parameters
I am simulating Naca 0012 airfoil in 2D with with 10 degrees of angle of attack. I donīt know where I have to check the values obtained for cl and cd. In the picture attached I show where I am checking the results. Are those the correct values for cd and cl?? Or I have to go to: Reports-Forces.
Thank you very much.
Those two methods are giving same results, but with Results > Forces you can get accurate number.
And as seen, changes in Cd is of order of 1e-7, which is negligible.
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