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NK-39

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AKA: 11D113. Status: Development ended 1971. Date: 1969-74. Thrust: 402.00 kN (90,373 lbf). Unfuelled mass: 631 kg (1,391 lb). Specific impulse: 352 s. Burn time: 1,200 s. Diameter: 1.30 m (4.20 ft).

After initial failures of the N-1 Kuznetsov developed modified versions of engines for all 3 stages, with multiple ignition capability and increased operational lifetime. These engines were never flown and were mothballed after the cancellation of the N1.

Engine: 631 kg (1,391 lb). Chamber Pressure: 98.00 bar. Area Ratio: 114. Thrust to Weight Ratio: 64.97. Oxidizer to Fuel Ratio: 2.6.