I'm trying to generate a round trailing edge for an airfoil with either no trailing edge or a sharp trailing edge. I do this by chopping off the end of the airfoil, taking 2 points each from the upper and lower sides, and then using this with the location of the trailing edge (1,0 usually) to generate a conic section in the form of Ax^2 + Bxy + Cx^2 + Dx + Ey + F = 0.
Then, I generate some x values and the corresponding y values from WolframAlpha's Solution. This works very well for some airfoils - but for some the contents of the square root are negative for some x values. How can I handle this? Does anyone understand how WolframAlpha solved the equation for y?
Use complex numbers.
For Quadratic Equations (herein $y$), there is a predetermined formula
Both can be easily read up on Wikipedia.