Abstract: A navigation system for an aircraft includes one or more wing-mounted sensors whose outputs are effected by the flexing of the wing during flight. The navigation system corrects for these errors using measurements of actual wing flex taken during an initial flight and thereafter assumed to be valid for all subsequent flights and for all aircraft using the same type of airframe. The actual measurements of wing flex define a wing flex correction factor that the navigation system may adjust during flight to reduce or remove residual errors. The wing flex correction factor accounts for all three types of possible wing flex: pitch, roll, and yaw flexing.