J-2X
| Use attributes for filter ! | |
| Thrust-to-weight ratio | 55. 04 |
|---|---|
| Nozzle ratio | 92:1 |
| Thrust (vac.) | 1,307 kN (294,000 lbf) |
| Mixture ratio | 5. 5-4. 5 |
| Cycle | Gas generator |
| Dry weight | 5,450 pounds (2,470 kg) |
| Date of Reg. | |
| Date of Upd. | |
| ID | 2477648 |
About J-2X
The J-2X is a liquid-fueled cryogenic rocket engine that was planned for use on the Ares rockets of NASA's Constellation program, and later the Space Launch System.
