Engine Model: L-7.70. Propellants: Lox/Kerosene. Thrust(vac): 37,007.000 kN (8,319,504 lbf). Isp: 335 sec. Isp (sea level): 310 sec. Burn time: 203 sec. Chambers: 1. Country: USA. Status: Study 1963. Engines used in recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange.
L-7.70 used on Rocket Stages