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RD-0126E
Part of RD-0126
Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump.

AKA: RO-97E. Status: Design concept 1998-. Date: 1998-. Thrust: 39.20 kN (8,813 lbf). Specific impulse: 472 s.

Engine: 234 kg (515 lb). Chamber Pressure: 70.00 bar.

Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau.
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