Merlin 1Cvac (original) (raw)

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Merlin 1Cvac

Part of Merlin

SpaceX LOx/Kerosene rocket engine. Hardware. Upper stage version of the Merlin developed for the Falcon 9 second stage. Based on the Merlin 1C and using a regeneratively cooled combustion chamber. First flight 2009.

AKA: Merlin 1V. Status: Hardware. Date: 2006-2009. Thrust: 411.40 kN (92,486 lbf). Specific impulse: 342 s. Burn time: 360 s.

However, the vacuum engine featured a larger exhaust section than the Merlin 1C and a much larger radiatively cooled expansion nozzle, in order to maximize performance in the vacuum of space.

Propellant Formulation: Lox/RP-1. Chamber Pressure: 40.81 bar. Area Ratio: 8.2. Thrust to Weight Ratio: 70.66.

Country: USA. Propellants: Lox/Kerosene. Agency: SpaceX.

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