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RD-0245-HC
Part of RD-0245 Family
Kosberg LOx/Kerosene rocket engine. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Status: Design concept 1990's. Thrust: 214.00 kN (48,109 lbf). Unfuelled mass: 290 kg (630 lb). Specific impulse: 320 s.

Chambers: 4. Engine: 290 kg (630 lb). Chamber Pressure: 142.00 bar. Thrust to Weight Ratio: 75.24. Oxidizer to Fuel Ratio: 2.3.



Country: Russia. Propellants: Lox/Kerosene. Agency: Kosberg bureau.

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