Engine Performance
|
RD-180 |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Rocket Propellant (RP) |
| Engine Cycle: |
Staged Combustion |
| Average Thrust: |
860,400 lb SL /
933,000 lb vac
3,820 kN / 4,142 kN |
| Chamber Pressure: (Pc) |
3,734 psia |
| Mixture Ratio: |
2.6 : 1 |
| Isp: |
311 sec SL
337 sec vac |
| Nozzle Area Ratio: |
36.4 : 1 |
| Gimbal Capability: |
8 degrees |
| Engine Mass: |
11,675 lb (dry)
5,307 kg (dry) |
| Engine Thrust to Weight |
80 |
| Mixture Ratio Control: |
Yes (EMA) |
| Throttle Range: (% Pc) |
50 - 100 % |
| Restart Capability: |
No |
Engine Size:
Length / Diameter |
13.0 /
9.8 ft
4.0 / 3.0 m |
| Flight Status |
Flight Qualified |
| Launch Vehicles: |
Atlas III & Atlas V (EELV) first stage |
* Performance and images provided by Pratt
& Whitney
|
