Depending on the location of the launch site and the inclination of the polar orbit, the launch vehicle may lose up to 460 m/s of Delta-v, approximately 5% of the Delta-v required to attain Low Earth orbit.
[2] The Iridium satellite constellation uses a polar orbit to provide telecommunications services.
However, very low orbits rapidly decay due to drag from the atmosphere.
[3] The half-orbit on the Sun side then takes only 50 minutes, during which local time of day does not vary greatly.
Because of Earth's equatorial bulge, an orbit inclined at a slight angle is subject to a torque, which causes precession.