J-2-SL

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J-2-SL

Part of J-2

Rocketdyne LOx/LH2 rocket engine. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use.

Status: Study 1966. Thrust: 996.70 kN (224,067 lbf). Unfuelled mass: 1,360 kg (2,990 lb). Specific impulse: 390 s. Specific impulse sea level: 275 s. Burn time: 310 s.

Thrust (sl): 729.300 kN (163,953 lbf). Thrust (sl): 74,366 kgf. Engine: 1,360 kg (2,990 lb). Chamber Pressure: 30.00 bar. Area Ratio: 14. Thrust to Weight Ratio: 74.73.

Country: USA. Launch Vehicles: Saturn INT-19. Propellants: Lox/LH2. Stages: Saturn II-SL. Agency: Rocketdyne.

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