| Aircraft Engine Manufacturer |
Armstrong Siddeley |
BMW |
| Aircraft Engine Type |
Turbojet |
Rocket |
| Dry Weight (kg) |
249.0222 |
|
| Diameter (mm) |
623.57 |
|
| Length (mm) |
1625.6 |
|
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/Armstrong_Siddeley_Viper |
en.wikipedia.org/wiki/BMW_109-718 |
| Fuel |
AVTUR, AVTAG |
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 |
Annular, 24 burners |
Catalyst ignited or Hypergolic combustion in a single combustion chamber |
| Afterburner |
No |
No |
| Streams |
1 |
1 |
| Maximum Takeoff Thrust (kN) |
12 |
12.2625 |
| Thrust To Weight |
4.9 |
|
| Specific Fuel Consumption (g/(kN·s)) |
|
15.89 |
| Compressor Description |
Seven stage axial |
|
| Turbine Description |
Single stage |
|