I'm trying to decide what to do with this, I'll probably post code somewhere eventually.
Some technical details: this is using the "
panel method", which means it's solving linearized equations that have some limitations.
It's subsonic only, no compression effects, no shock waves, etc.
It needs some hints to know what to do with trailing vortexes on lifting surfaces, so it's not good at modeling details of wingtip shape effects.
It's inviscid, so it has no natural notion of how to handle drag effects, and needs some hacks added in to have realistic flow around the back end.
Since wing stall is a combination of viscous and vortex effects, it's bad at modeling forces on a stalled wing (including fins at high angles of attack)
It does give plausible lift force data, which includes reaction forces from fins at moderate angles of attack.
Using the pressure distribution from the lifting forces it's possible to compute torques around the center of gravity, which should give basically the same information as CP calculations. I'm thinking about how to represent this well, which is a bit tricky because "Center of Pressure" isn't really a mathematically well-defined concept -- it's an engineering approximation that works well enough for some kinds of symmetric geometries.
