Raptor
Type: Lower Stage Engine and Upper Stage Variant
Country of Origin: United States
Manufacturer: SpaceX
First Flight:
Status: In development
Propellant (O/F): Liquid Oxygen/Liquid Methane
Mixture Ratio (O/F by mass): 3.8
Cycle: Full-flow Staged Combustion
Chambers: 1
Thrust (vac.): 3285 kN; 3500 kN (Raptor Vacuum)
Thrust (s.l.): 3050 kN
Throttle:
ISP (vac.): 361 s; 382 s (Raptor Vacuum)
ISP (s.l.): 334 s
Chamber Pressure: 4400 psi
Nozzle Ratio: 40:1; 200:1 (Raptor Vacuum)
Burn time:
Ignitions:
Mass:
Length:
Diameter: less than 2 meters; around 4 meters (Raptor Vacuum)
Used in: SpaceX ITS
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