Hello, fellows CFX users. I'm currently realising a project using CFX 5.5.1 on a Unix Platform. I work on the aerodynamic performance of an airfoil with step-induced vortex for lift augmentation. My problem is that I'm trying to find a way to extract the lift coefficient, drag coefficient and lift-to-drag ratio out of the results; however I haven't suceeded yet. Can anybody help me?
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