RL10
| Use attributes for filter ! | |
| Nozzle ratio | 84:1 or 280:1 |
|---|---|
| Thrust (vac.) | 110. 1 kN (24,800 lbf) |
| Mixture ratio | 5. 88:1 |
| Cycle | Expander cycle |
| First flight | 1962 (RL10A-1) |
| Dry weight | 301 kg (664 lb) |
| Date of Reg. | |
| Date of Upd. | |
| ID | 2477059 |
About RL10
The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN of thrust per engine in vacuum.
