User:Singularities421/sandbox
The XRS-2200 was a linear aerospike rocket engine using a gas generator cycle developed by Aerojet Rocketdyne during the 1990s for use on the Lockheed X-33 single-stage-to-orbit lifting body demonstrator.[1][2] The X-33 was to use 2 X-33 engines.
 An XRS-2200 being tested at Stennis Space Centre. | |
| Country of origin | United States |
|---|---|
| Manufacturer | Rocketdyne |
| Status | Cancelled |
| Liquid-fuel engine | |
| Propellant | LH2/LOX |
| Mixture ratio | 6:4.5 |
| Cycle | Gas generator |
| Configuration | |
| Nozzle ratio | 57.7:1 |
| Performance | |
| Thrust, vacuum | 1184kN (266,230 lbf) |
| Thrust, sea-level | 909kN (204,420lbf) |
| Throttle range | 50-100% |
| Chamber pressure | 857 pounds per square inch (5.91 MPa) |
| Specific impulse, vacuum | 437s |
| Specific impulse, sea-level | 339s |
| Dimensions | |
| Measurement | 134 inches (3.4 m)*, 42 inches (1.1 m)*, 90 inches (2.3 m)* |
| Used in | |
| Lockheed X-33 | |
| References | |
| References | https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20020017580.pdf |