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

Status: Design concept 1994. Thrust: 110.80 kN (24,909 lbf). Unfuelled mass: 317 kg (698 lb). Specific impulse: 450 s. Burn time: 630 s. Diameter: 2.44 m (8.00 ft).

Engine: 317 kg (700 lb). Chamber Pressure: 102.00 bar. Area Ratio: 190. Thrust to Weight Ratio: 50. Coefficient of Thrust vacuum: 1.12.

Country: USA. Propellants: Lox/LH2. Stages: Centaur C-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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