| Aircraft Engine Manufacturer |
BMW |
Lyulka-Saturn |
| Aircraft Engine Type |
Rocket |
Turbojet |
| Dry Weight (kg) |
|
885 |
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/BMW_109-718 |
en.wikipedia.org/wiki/Lyulka_TR-1 |
| Fuel |
Diesel fuel and red fuming nitric acid (RFNA / S-Stoff) oxidiser with injected catalyst or R-stoff / SV-stoff fuel and … |
|
| Geared Fan |
No |
No |
| Combustion Chamber |
Catalyst ignited or Hypergolic combustion in a single combustion chamber |
|
| Afterburner |
No |
No |
| Streams |
1 |
1 |
| Maximum Takeoff Thrust (kN) |
12.2625 |
12.8 |
| Thrust To Weight |
|
1.47 |
| Specific Fuel Consumption (g/(kN·s)) |
15.89 |
3653.925 |
| Compressor Description |
|
eight-stage axial-flow |
| Turbine Description |
|
single stage |