| BMW 109-558 ✕ | |
|---|---|
| Aircraft Engine Manufacturer | BMW |
| Aircraft Engine Type | Rocket |
| Dry Weight (kg) | 160 |
| Diameter (mm) | 1250 |
| Length (mm) | 2400 |
| Wikipedia Article (URL) | en.wikipedia.org/wiki/BMW_109-558 |
| Fuel | R-Stoff fuel (50% triethylamine and 50% xylidine) and SV-Stoff oxidiser (94% nitric acid with 6% dinitrogen tetroxide) |
| Geared Fan | No |
| Combustion Chamber | Hypergolic combustion in a single combustion chamber |
| Afterburner | No |
| Streams | 1 |
| Maximum Takeoff Thrust (kN) | 3.7 |
| Thrust To Weight | 0.0231 |