Merlin
From OrbiterWiki
| Merlin | |
|---|---|
| |
| Overview | |
| Vacuum thrust | 409 kN |
| Sealevel thrust | 342 kN |
| specific impulse (vac) | 3.0 kN·s/kg |
| Fuel | RP-1 |
| Oxidizer | LOX |
| Cycle | gas-generator cycle |
| First flight | 2006 |
| Entered service | Not in service |
| Manufacturer | SpaceX |
| Dimensions | |
| Length | Unknown |
| Width | Unknown |
| Dry mass | approx. 400 kg |
| Power head | |
| Chamber pressure | 6.14 MPa |
| Chamber temperature | Unknown |
| Fuel flow rate | Unknown |
| Oxidizer flow rate | Unknown |
The Merlin engine is a RP-1/liquid oxygen gas-generator cycle rocket engine. The Merlin engine was developed for use on the Falcon 1, Falcon 5 and Falcon 9 rockets by SpaceX and is designed for sea recovery and reuse.
[edit] Engine details
The nozzle is an inexpensive, expendable ablatively cooled carbon fiber composite.
Engine revision 1B has been enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW)
[edit] Performance
Current published ratings:
| General engine data | |
|---|---|
| Manufacturer | SpaceX |
| engine cycle | gas-generator cycle |
| Performance | |
| Sea level thrust | 342 kN (77,000 lbf) |
| Vacuum thrust | 409 kN (92,000 lbf) |
| Sea level Isp | 2.6 kN·s/kg (255 s) |
| Vacuum Isp | 3.0 kN·s/kg (304 s) |
| Chamber pressure | 6.14 MPa (890 psi) |
| Propellants | |
| Fuel | RP-1 rocket grade kerosene |
| Oxidizer | Liquid oxygen |
| Other information | |
| Engine mass | approx. 435 kg |
| Thrust-to-weight ratio (fully accounted) | 96 |
