మూస:Infobox rocket stage

**S-II**
	; The Apollo 6 S-II stage during stacking operations in the VAB
Manufacturer	North American
Country of origin	USA
Used on	Saturn V (stage 2); Saturn INT-21 (stage 2)
General Characteristics
Height	24.9 m (82 ft)
Diameter	10 m (33 ft)
Mass	480,900 kg (1,060,000 lb)
Propellant mass	444,000 kg (970,000 lb)
Engine details
Engines	5 J-2 engine
Thrust	5,115 kN
Burn time	367 seconds
Fuel	LOX/LH2

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{{Infobox rocket stage
|name = S-II
|image = ap6-MSFC-6758331.jpg
|caption = The [[Apollo 6]] S-II stage during stacking operations in the [[Vehicle Assembly Building|VAB]]
|manufacturer = [[North American Aviation|North American]]
|country = USA
|rockets = [[Saturn V]] (stage 2)<br>[[Saturn INT-21]] (stage 2)
|height = 24.9 m
|alt-height = 82 ft
|diameter = 10 m
|alt-diameter = 33 ft
|mass = 480,900 kg
|alt-mass = 1,060,000 lb
|propmass = 444,000 kg
|alt-propmass = 970,000 lb
|engines = 5 [[J-2 (rocket engine)|J-2]] engine
|thrust = 5,115 kN
|alt-thrust = 1,150,000 lbf
|time = 367 seconds
|fuel = [[Liquid oxygen|LOX]]/[[Liquid hydrogen|LH<sub>2</sub>]]
}}

v t e Spaceflight and rocketry infoboxes
Generic	space agency space program spacecraft class spaceflight
Human spaceflight	astronaut space shuttle space station module
Rocketry	launch pad launch pad/pad rocket engine launch stage weapon
Other	year in spaceflight
See also Category:Spaceflight infobox templates {{Spaceflight navboxes}}

General Characteristics
The Apollo 6 S-II stage during stacking operations in the VAB
Manufacturer	North American
Country of origin	USA
Used on	Saturn V (stage 2) Saturn INT-21 (stage 2)
Height	24.9 m (82 ft)
Diameter	10 m (33 ft)
Mass	480,900 kg (1,060,000 lb)
Propellant mass	444,000 kg (970,000 lb)
Engine details
Engines	5 J-2 engine
Thrust	5,115 kN
Burn time	367 seconds
Fuel	LOX/LH₂

మూస:Infobox rocket stage

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See also