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H-1b
Part of LR79
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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