Great work! I don't quite understand the method, though. How is it that you can simultaneously satisfy the flow boundary conditions (flow tangency over each panel) while also fitting the cl-alpha behavior of the 2D airfoil sections? If you introduce a virtual twist to the airfoil sections to satisfy the 2D cl-alpha curve, aren't you in turn changing the VLM solution so that flow tangency is no longer satisfied (the flow would now be tangent to the new virtually twisted surface, not the original surface)? In other words, the system would seem to be over-constrained since the VLM has a unique solution of vortex strengths that satisfies the flow boundary conditions.
Great work! I don't quite understand the method, though. How is it that you can simultaneously satisfy the flow boundary conditions (flow tangency over each panel) while also fitting the cl-alpha behavior of the 2D airfoil sections? If you introduce a virtual twist to the airfoil sections to satisfy the 2D cl-alpha curve, aren't you in turn changing the VLM solution so that flow tangency is no longer satisfied (the flow would now be tangent to the new virtually twisted surface, not the original surface)? In other words, the system would seem to be over-constrained since the VLM has a unique solution of vortex strengths that satisfies the flow boundary conditions.