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L-6.55
Notional LOx/Kerosene rocket engine. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange.

Status: Study 1963. Thrust: 31,010.00 kN (6,971,320 lbf). Specific impulse: 330 s. Specific impulse sea level: 310 s. Burn time: 203 s.



Country: USA. Launch Vehicles: Nova GD-J. Propellants: Lox/Kerosene. Stages: Nova GD-J-1.

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