H-1
Type: Lower Stage Engine
Country of Origin: United States
Manufacturer: Rocketdyne
First Flight: 1963
Status: Retired
Propellant (O/F): Liquid Oxygen/Kerosene
Mixture Ratio (O/F by mass):
Cycle: Gas generator
Chambers: 1
Thrust (vac.):
Thrust (s.l.): 900 kN
Throttle: none
ISP (vac.): 289 s
ISP (s.l.): 255 s
Chamber Pressure: 700 psi
Nozzle Ratio:
Burn time: 155 sec
Ignitions: 1
Mass: 1000 kg
Length: 2.68 m
Diameter: 1.49 m
Used in: Saturn I, Saturn IB
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