Walter HWK turbopump
Ignition sequence
STAGE 3 (HAUPTSTUFE): Full 550 HP turbine output (3,800 RPM)! Pumps deliver 125 kg/sec at 2.4 MPa (24 bar) for 25.4 tonnes liftoff thrust.
Live telemetry
RPM Fuel MPa LOX MPa
Turbine
3,800 RPM
550 HP (405 kW)
Pump outlet
2.42 MPa
24.2 bar (350 psi)
Steam generator
420 °C
H₂O₂ + Z-Stoff 2.1 kg/s
Mass flow
125.0 kg/s
56 fuel + 69 LOX
Engine lab
Fuel and nozzle
Oxygen : fuel 1.23
Nozzle size 3.4×
Flying at
Thrust
245 kN
Efficiency (Isp)
200 s
Chamber
15 bar
pressure
Flame
2,700 °C
gas temperature
Burn time
68 s
Thrust while climbing — this engine- - V-2
Simplified textbook model: same pumps (125 kg/s), ideal-gas nozzle equations. Good for comparing, not exact figures.
V-2 Engineering Lab · simplified teaching models, figures rounded