This page no longer updated from 31 October 2001. Latest version can be found at RD-0210-HC

Manufacturer Name: RD-0210-HC. Designer: Kosberg. Propellants: Lox/Kerosene Thrust(vac): 60,367 kgf. Thrust(vac): 592.00 kN. Isp: 342 sec. Mass Engine: 570 kg. Chambers: 1. Chamber Pressure: 147.00 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Design concept 1990's. References: 342 . Comments: Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
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Last update 12 March 2001.
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© Mark Wade, 2001 .