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RL-10B-X


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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 RL-10B-X Part of RL-10 Pratt and Whitney LOx/LH2 rocket engine. Design concept 1994.

Status: Design concept 1994. Thrust: 93.40 kN (20,997 lbf). Unfuelled mass: 317 kg (698 lb). Specific impulse: 470 s. Burn time: 408 s. Diameter: 1.53 m (5.00 ft).

Engine: 317 kg (700 lb). Chamber Pressure: 102.04 bar. Area Ratio: 250. Thrust to Weight Ratio: 30. Coefficient of Thrust vacuum: .67.

Country: USA. Propellants: Lox/LH2. Stages: Centaur B-X. Agency: Pratt and Whitney. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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