SpaceX_Raptor
| Status | Under development |
|---|---|
| Propellant | Liquid oxygen / liquid methane |
| Chamber pressure | 300 bar (30 MPa; 4,400 psi)[6][7] 330 bar (33 MPa; 4,800 psi)[3] (~ 7s test) |
| Mixture ratio | 3.55[1][2] |
| Thrust-to-weight ratio | 200 (goal)[5] |
| Isp (vac.) | 380 s (3,700 m/s) (goal)[6] |
| Cycle | Full-flow staged combustion |
| Dry weight | 1,500 kg (3,300 lb) (goal)[10] |
| Nozzle ratio | 40 |
| Country of origin | United States |
| Length | 3.1 m (10 ft)[8] |
| Isp (SL) | 330 s (3,200 m/s)[6] |
| Pumps | 2 turbopumps |
| Manufacturer | SpaceX |
| Chamber | 1 |
| Application | 1st and 2nd stage propulsion of the Starship vehicle |
| Diameter | 1.3 m (4 ft 3 in)[9] |
| Thrust | 2,200 kN (500,000 lbf) max[3] 880 kN; 200,000 lbf (90 tf) min (40%)[4] |
