| Aircraft Engine Manufacturer |
BMW |
Heinkel-Hirth |
| Aircraft Engine Type |
Rocket |
Turbojet |
| Dry Weight (kg) |
|
950 |
| Diameter (mm) |
|
875 |
| Length (mm) |
|
3405 |
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/BMW_109-718 |
en.wikipedia.org/wiki/Heinkel_HeS_011 |
| 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 |
16 chamber annular |
| Afterburner |
No |
No |
| Streams |
1 |
1 |
| Maximum Takeoff Thrust (kN) |
12.2625 |
12.7 |
| Thrust To Weight |
|
1.38 |
| Specific Fuel Consumption (g/(kN·s)) |
15.89 |
|
| Compressor Description |
|
Diagonal + 3-stage axial |
| Turbine Description |
|
2-stage axial |