Engine Model: L-6.55. Propellants: Lox/Kerosene. Thrust(vac): 31,010.000 kN (6,971,320 lbf). Isp: 330 sec. Isp (sea level): 310 sec. Burn time: 203 sec. Chambers: 1. Country: USA. Status: 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.
L-6.55 used on Rocket Stages