Maximum Takeoff Thrust
3.7 kN
Architecture
| Fan |
Fan Stages
—
|
Fan Blades
—
|
Fan Technology
—
|
Fan Pressure Ratio
—
|
| Gearbox |
Geared Fan
No |
Gear
—
|
Reduction Ratio
—
|
| LP compressor |
Low-Pressure Compressor Stages
—
|
Low-Pressure Compressor Technology
—
|
BP Compressor Pressure Ratio
—
|
| IP compressor |
Intermediary-Pressure Compressor Stages
—
|
Intermediary-Pressure Compressor Technology
—
|
IP Compressor Pressure Ratio
—
|
| HP compressor |
High-Pressure Compressor Stages
—
|
High-Pressure Compressor Technology
—
|
HP Compressor Pressure Ratio
—
|
| Combustor |
Combustion Chamber
Hypergolic combustion in a single combustion chamber |
| HP turbine |
High Pressure Compressor Stages
—
|
High-Pressure Turbine Technology
—
|
| IP turbine |
Intermediary-Pressure Turbine Stages
—
|
Intermediary-Pressure Turbine Technology
—
|
| LP turbine |
Low-Pressure Turbine Stages
—
|
Low-Pressure Turbine Technology
—
|
| Whole engine |
Streams
1 |
Bypass Ratio
—
|
Overall Pressure Ratio
—
|
Afterburner
No |
Pictures
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All data (14 fields)
- Name
- 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