J-2
Type: Upper Stage Engine
Country of Origin: United States
Manufacturer: Rocketdyne
First Flight: February 26, 1966
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 4.5 to 5.5
Cycle: Gas-generator
Chambers: 1
Thrust (vac.): 1033.1 kN
Thrust (s.l.): 486.2 kN
Throttle: 75% to 100% (by varying mixture ratio)
ISP (vac.): 421 s
ISP (s.l.): 200 s
Chamber Pressure: 763 psi (52.6 bar)
Nozzle Ratio: 27.5:1
Burn time: 500 sec.
Ignitions: 2+
Mass: 1788.1 kg
Length: 3.4 m
Diameter: 2.1 m
Used in: Saturn IB, Saturn V
Links: