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Manufacturer Name: RD-0126A. Other Designations: RO-97A. Designer: Kosberg. Developed in: 1996-. Application: upper stage. Propellants: Lox/LH2 Thrust(vac): 10,000 kgf. Thrust(vac): 98.00 kN. Isp: 476 sec. Mass Engine: 340 kg. Length: 2.7 m. Chambers: 1. Chamber Pressure: 118.00 bar. Oxidizer to Fuel Ratio: 6.00. Country: Russia. Status: Design concept 1996-. References: 342 . Comments: Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.
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Last update 12 March 2001.
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