I have modelled a wing with anhedral arc and loft toward the wingtips. The cross-section is sketched using the 4 digit NACA formula within Equation Driven Curve. Using Eq Driven Curve as opposed to Curve through X,Y,Z, gives me the ability to use 'Driving Dimensions' as parameters within the equation, allowing a parametric shape optimisation within ANSYS DesignXplorer.
My issue is that I can find no way of adjusting the camber of the airfoil cross-section. In order to account for the camber correctly, I must use a 'Piecewise Function' i.e. using a particular formula for the sketch line from x1=0% of chord length, to x2= position of max camber as % of chord length, and a separate formula for the line from x2 until x3= 100% of chord length ('x' being the horizontal coordinate).
Any help/advise concerning how to do this would be really appreciated, as I seem to have hit a brick wall. Thanks
I've attached the camber formula below for clarification: