Walter HWK 109-500

Dry Weight
125 kg
Thrust To Weight
2

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 catalytic decomposition of hydrogen peroxide (80% H2O2) in a single decomposition chamber without combustion.
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

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All data (11 fields)
Name
Walter HWK 109-500
Aircraft Engine Manufacturer
Walter (HWK)
Aircraft Engine Type
Rocket
Dry Weight (kg)
125
Wikipedia Article (URL)
en.wikipedia.org/wiki/Walter_HWK_109-500
Fuel
T-Stoff monopropellant - (80% hydrogen peroxide oxidiser catalysed by Z-Stoff permanganate catalyst)
Geared Fan
No
Combustion Chamber
catalytic decomposition of hydrogen peroxide (80% H2O2) in a single decomposition chamber without combustion.
Afterburner
No
Streams
1
Thrust To Weight
2