Engine Performance
|
RS-27A |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Kerosene (RP) |
| Engine Cycle: |
Gas Generator |
| Average Thrust: |
200,000 lb SL /
244,100 lb vac
889.6 kN SL / 1,085.8 kN vac |
| Chamber Pressure: (Pc) |
702 psia |
| Mixture Ratio: |
2.24 : 1 |
| Isp: |
254.2 sec SL
301.7 sec vac |
| Nozzle Area Ratio: |
12 : 1 |
| Gimbal Capability: |
No |
| Engine Mass: |
2,528 lb
1,146 kg |
| Engine Thrust to Weight |
96.6 |
| Mixture Ratio Control: |
--- |
| Throttle Range: (% Pc) |
100% (only) |
| Restart Capability: |
No |
Engine Size:
Length / Diameter |
12.4 ft / 5.6 ft
3.8 m / 1.7 m |
| Flight Status |
Flight Qualified |
| Launch Vehicles: |
Delta II and Delta III First Stage |
* Engine performance from Boeing Delta II
and Delta III Reference Data Sheets and Boeing Web Site.
|
