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L-7.70
Notional LOx/Kerosene rocket engine. 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.

Status: Study 1963. Thrust: 37,007.00 kN (8,319,504 lbf). Specific impulse: 335 s. Specific impulse sea level: 310 s. Burn time: 203 s.

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