Latitude = 2nR/T, where T is 24 h (i.e. the period of one revolution)
Hence, T2 is proportional to R3. This is Kepler's Third Law of planetary motion and holds for a satellite around the Earth as it does for a planet around the Sun.
Geostationary orbits are, however, limited to the equator and the same part of the Earth's surface may not always wish to be viewed, e.g. a military satellite will want to examine different parts of the Earth's surface as conflicts and battle fronts develop. Thus, alternative orbiting patterns may be used.