S-3 (original) (raw)

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S-3

Part of LR79

S-3B engine
Credit: USAF

Rocketdyne LOx/Kerosene rocket engine. Juno II, Saturn A-2 studies of 1959. First flight 1958.

Status: First flight 1958. Number: 10 . Thrust: 758.70 kN (170,563 lbf). Unfuelled mass: 725 kg (1,598 lb). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 182 s. Diameter: 2.67 m (8.75 ft).

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 725 kg (1,598 lb). Chamber Pressure: 39.50 bar. Area Ratio: 8. Thrust to Weight Ratio: 106.713103448276. Coefficient of Thrust vacuum: 1.71921743620711. Coefficient of Thrust sea level: 1.51668579063749.

Country: USA. Launch Vehicles: Juno II, Saturn A-2. Propellants: Lox/Kerosene. Stages: Jupiter Cluster, Jupiter (stage). Agency: Rocketdyne.

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