This page no longer updated from 31 October 2001. Latest version can be found at RD-0242-HC

Manufacturer Name: RD-0242-HC. Designer: Kosberg. Developed in: 1998-. Propellants: Lox/Kerosene Thrust(vac): 12,746 kgf. Thrust(vac): 125.00 kN. Isp: 312 sec. Mass Engine: 120 kg. Chambers: 1. Chamber Pressure: 196.20 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Developed 1998-. References: 342 . Comments: Proposed variant of RD-0242 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 .