Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
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.

Back to top of page
Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2019 Mark Wade - Contact
© / Conditions for Use