Engine Performance
|
RS-68 |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
| Engine Cycle: |
Gas Generator |
| Average Thrust: |
650,000 lbf SL
/ 745,000 lbf vac
2,886kN / 3,308 kN |
| Chamber Pressure: (Pc) |
1,410 psia |
| Mixture Ratio: |
6 : 1 |
| Isp: |
365 sec SL /
410 sec vac |
| Nozzle Area Ratio: |
21.5 |
| Gimbal Capability: |
yes (hydraulic) |
| Engine Mass: |
14,560 lb
6,600 kg |
| Engine Thrust to Weight |
51.2 |
| Mixture Ratio Control: |
--- |
| Throttle Range: (% Pc) |
60 to 100%
(estimated) |
| Restart Capability: |
No |
Engine Size:
Length / Width |
--- |
| Flight Status |
Qualification |
| Launch Vehicles: |
Delta IV (EELV) |
* Engine performance from Boeing web site
|
