N1M 1965

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N1M 1965 - A

Part of N1 Block A

LOx/Kerosene propellant rocket stage. As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 metric tons thrust to 250 metric tons.

Status: Study 1965. Thrust: 85,300.00 kN (19,176,200 lbf). Gross mass: 3,800,000 kg (8,300,000 lb). Unfuelled mass: 375,000 kg (826,000 lb). Specific impulse: 330 s. Specific impulse sea level: 296 s. Burn time: 130 s. Height: 50.00 m (164.00 ft). Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft).

No Engines: 30.

Country: Russia. Engines: 11D51M. Launch Vehicles: N-IM 1965, N-IMV-III, N-IMV-II-III. Propellants: Lox/Kerosene.

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