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S1.5400A
Part of S1 Family
Korolev LOx/Kerosene rocket engine. Molniya 8K78M-3. First flight 1964.

AKA: 11D33M. Date: 1961-64. Number: 294 . Thrust: 67.30 kN (15,130 lbf). Unfuelled mass: 148 kg (327 lb). Specific impulse: 342 s. Burn time: 200 s.

Engine: 148 kg (327 lb). Chamber Pressure: 54.00 bar. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 46.25.



Country: Russia. Launch Vehicles: Molniya 8K78M. Propellants: Lox/Kerosene. Stages: Molniya 8K78M-3. Agency: Korolev bureau.

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