The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.

The S-II, the second stage of the Saturn V rocket, was the largest liquid hydrogen stage produced in the 1960s. Equipped with five J-2 rocket engines, it produced about 1,000,000 pounds of thrust. It was 33 feet in diameter and 81 ft. 7 in. high.

The spray-on insulation debuted on S-II-8 (Apollo 13), and was used for the final six flight stages which actually flew; the two unused S-II flight stages also used the spray-on foam. The Saturn V Launch Vehicle Flight Evaluation Report AS-508 (Apollo 13 Mission) notes this debut its "S-II Significant Configuration Changes" section:

Saturn II proposals: INT-17, INT-18, INT-19. The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under a NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program. [1] .

Feb 19, 2017 · Stages of the Apollo stack (at least the configuration that landed humans on the Moon) are identified as S-IC, S-II, and S-IVB for the first, second, and third stages. There's no S-III. Why the gap in numbering? Was Saturn going to be a …

Volume 1: Introduction contains a general description of the S-II stage, the various phases of the S-II's flight, and an overview of the S-II stage displays at the MSC. It also contains information about the course which was to have been presented.

The Saturn V's S-II stage was located in the museum's Rocket Park from June 28, 1969 (the day it was transferred from Marshall Space Flight Center) until July 13, 2007 (the day it was moved into the Davidson Center for Space Exploration).

Nov 19, 2009 · This is a view of the Saturn S-II (second) stage being assembled in the vertical assembly building at North American Aviation in Seal Beach, California. The hydrogen tank is lowered onto the liquid oxygen tank and their common bulkhead.

LOx/LH2 propellant rocket stage. Early design version for use with Saturn I first stage. Status: Study 1960. Thrust: 3,557.31 kN (799,716 lbf). Gross mass: 100,000 kg (220,000 lb). Unfuelled mass: 14,000 kg (30,000 lb). Specific impulse: 420 s. Specific impulse sea level: 300 s. Burn time: 100 s. Height: 22.56 m (74.01 ft). Diameter: 6.60 m (21 ...

It is six minutes that S-II is used after the separation of the S-IC. By using this power, APOLLO is lifted from 200,000 feet (60km) to about 606,000 feet (184km). S-II structure consists of five units of Forward Skirt, LH2 Tank, LOX Tank, Aft Skirt and Thrust Structure, Aft Interstage from the top.