Calculating Induced Drag in Panel Flow
I am using Caedium Panel Flow to model a wing section for a sailplane as part of my undergraduate project. I have completed the NACA 4415 tutorial and understand how to calculate Cp, but I want to get the induced drag distribution too for my wing section too.
Is there a way to calculate this using Caedium? Also, can I import Autocad (.dwg, .dxf) files into Panel Flow to be solved?
Any assistance would be greatly appreciated.