PF RP-1

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PF RP-1

Notional LOx/Kerosene rocket engine. Study 1967. Used on Saturn LCB-LOx/RP-1 launch vehicle.

Status: Study 1967. Thrust: 20,306.00 kN (4,564,970 lbf). Specific impulse: 275 s. Specific impulse sea level: 253 s. Burn time: 163 s.

Country: USA. Launch Vehicles: Saturn LCB-Lox/RP-1. Propellants: Lox/Kerosene. Stages: Saturn LCB-Lox/RP-1 stage.

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