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RD-0126E


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A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z 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. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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