J-2X
Type: Upper Stage Engine
Country of Origin: United States
Manufacturer: Aerojet Rocketdyne
First Flight:
Status: Development halted
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.): 1307 kN
Thrust (s.l.):
Throttle: 75% to 100% (by varying mixture ratio)
ISP (vac.): 448 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 92:1
Burn time:
Ignitions:
Mass: 2470 kg
Length: 4.7 m
Diameter: 3 m
Used in:
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