J-2-SL

Designer: Rocketdyne. Propellants: Lox/LH2. Thrust(vac): 996.700 kN (224,067 lbf). Thrust(sl): 729.300 kN (163,953 lbf). Isp: 390 sec. Isp (sea level): 275 sec. Burn time: 310 sec. Mass Engine: 1,360 kg (2,990 lb). Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 14.00. Thrust to Weight Ratio: 74.73. Country: USA. Status: Study 1966.

Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use.

J-2-SL used on Rocket Stages

Used on stage: Saturn II-SL. on launch vehicle: Saturn INT-19.

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