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N1 Block B
LOx/Kerosene propellant rocket stage. Includes 3500 kg Stage 2-Stage 3 interstage. Compared to total fuelled mass excludes 1,000 kg in propellants lost to boil-off prior to stage ignition. Values as in draft project as defended on 2-16 July 1962.

Status: Retired 1972. Thrust: 14,039.98 kN (3,156,313 lbf). Gross mass: 560,700 kg (1,236,100 lb). Unfuelled mass: 55,700 kg (122,700 lb). Specific impulse: 346 s. Burn time: 120 s. Height: 20.50 m (67.20 ft). Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft).

No Engines: 8.

Subtopics
N1 1962 - B LOx/Kerosene propellant rocket stage. Includes 3500 kg Stage 2-Stage 3 interstage. Compared to total fuelled mass excludes 1,000 kg in propellants lost to boil-off prior to stage ignition. Values as in draft project as defended on 2-16 July 1962.
N-11 Block A LOx/Kerosene propellant rocket stage. Derived from N1 Block B, with large number of engines and expansion ratio adjusted for sea level operation. Includes 3500 kg Stage 2-Stage 3 interstage.
N1 1964 - B LOx/Kerosene propellant rocket stage. Second stage of the N1 superbooster. As per draft project for N1-L3, 1964. Specific impulse estimate down one second from 1962 draft project. Thrust said to be increased 2% but not reflected in figures given.
N1 Block V-II LOx/LH2 propellant rocket stage. N1 improvement study, 1965. LOx/LH2 replacement for Block B second stage.
N1F 1965 - B LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.
N1M 1965 - B LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Further stretch of Block B and thrust increased again to 280 metric tons per engine.
N1U 1965 - B LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
N1F Block B LOx/Kerosene propellant rocket stage. Includes 3,500 kg for Stage 2-3 interstage.
Country: Russia. Engines: NK-15V. Launch Vehicles: N1, N1 1969. Propellants: Lox/Kerosene.
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