Abstract: Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis.