What can be found by dividing the total moment by the total weight of an aircraft?

The center of gravity (CG) of an aircraft is determined by dividing the total moment by the total weight. This calculation provides the location of the CG in relation to a reference point, typically measured from the leading edge of the wing or another defined location. The moment is a product of the weight of each individual component and its distance from the reference point, summed for all components of the aircraft. By understanding where the CG is located, pilots and engineers can ensure that the aircraft is balanced for safe operation, which is crucial for stability and handling characteristics during flight.

The other options, while related to aircraft performance and aerodynamics, do not derive from this specific calculation. The center of pressure relates to the point where aerodynamic forces occur, the weight distribution refers to how the weight of the aircraft is distributed, and the center of lift is concerned with the aerodynamic lift generated by the wings. Each of these concepts plays a role in the overall performance and stability of the aircraft, but they are not directly calculated using the moment-to-weight ratio as the center of gravity is.