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astronautix.com RD-0256-HC


Manufacturer Name: RD-0256-HC. Designer: Kosberg. Developed in: 1996-. Propellants: Lox/Kerosene Thrust(vac): 83,617 kgf. Thrust(vac): 820.00 kN. Isp: 344 sec. Mass Engine: 770 kg. Chambers: 1. Chamber Pressure: 172.00 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Design concept 1996-. References: 342 . Comments: Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
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Last update 12 March 2001.
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