|
XRS-2200
(X-33 Engine) |
RS-2200
(VentureStar Engine) |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
| Engine Cycle: |
Gas Generator |
Gas Generator |
| Average Thrust: |
204,420 lbf SL /
266,230 lbf vac
907,624 N SL / 1,182 kN vac |
431,000 lbf SL /
495,000 lbf vac
1,914 kN SL / 2,198 kN vac |
| Chamber Pressure: (Pc) |
857 psia
59 bar |
2,250 psia
155 bar |
| Mixture Ratio: |
5.5 : 1 |
6 : 1 |
| Isp: |
339 sec SL
436.5 sec vac |
347 sec SL
455 sec vac |
| Nozzle Area Ratio: |
58 : 1 |
173 : 1 |
| Gimbal Capability: |
none
(some differential throttling capability ± 15%) |
none |
| Engine Mass: |
--- |
--- |
| Engine Thrust to Weight |
--- |
--- |
| Mixture Ratio Control: |
--- |
--- |
| Throttle Range: (% Pc) |
40 to 119% |
18 to 100% |
| Restart Capability: |
No |
No |
Engine Size:
Length / Width |
11.0 (max) / 7.3 ft
3.4 (max) / 2.2 m |
21.0 (max) / 7.75
ft
6.4 (max) / 2.4 m |
| Flight Status |
Qualification |
Concept |
| Launch Vehicles: |
X-33 |
VentureStar |
