Saturn V was developed for the Apollo Program and has three liquid propellant stages. The first stage (S-IC) is powered by five F-1 engines and burns liquid oxygen and kerosene. The second stage (S-1) is propelled by five J-2 engines and burns liquid oxygen and liquid hydrogen. The third stage (S-IVB) is propelled by a single J-2 engine and burns liquid oxygen and liquid hydrogen. The S-IVB stage has multiple burn capability. An instrument unit mounted on top of the S-IVB stage provides inertial navigation, guidance and flight control for all three stages.

A two-stage Saturn V configuration is to place the first U.S. manned scientific space station, Skylab I, with a mass of about 77,200 kilograms (170,000 lb mass) into a 435 kilometer (235 nautical mile) earth orbit.