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H-1b
Part of LR79 Family
Rocketdyne LOx/Kerosene rocket engine. First flight 1966.

Number: 72 . Thrust: 1,030.20 kN (231,598 lbf). Unfuelled mass: 988 kg (2,178 lb). Specific impulse: 296 s. Specific impulse sea level: 262 s. Burn time: 155 s. Height: 2.20 m (7.20 ft). Diameter: 0.82 m (2.67 ft).

Thrust (sl): 911.900 kN (205,003 lbf). Thrust (sl): 92,986 kgf. Engine: 988 kg (2,178 lb). Chamber Pressure: 48.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 106.329200404858. Coefficient of Thrust vacuum: 1.57681378520837. Coefficient of Thrust sea level: 1.4101471185417.



Country: USA. Launch Vehicles: Saturn B-1, Saturn A-2, Saturn IB, Saturn IB-C, Saturn IB-CE, Saturn IB-D, Saturn INT-11, Saturn INT-12, Saturn INT-13, Saturn INT-14, Saturn INT-15. Propellants: Lox/Kerosene. Stages: Saturn IB stage, Saturn IB-11, Saturn IB-15, Saturn S-1B-4. Agency: Rocketdyne.

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