NK-39

Manufacturer Name: NK-39. Government Designation: 11D113. Designer: Kuznetsov. Developed in: 1969-74. Application: N-1F stage 3 (block V). Propellants: Lox/Kerosene. Thrust(vac): 402.000 kN (90,373 lbf). Isp: 352 sec. Burn time: 1,200 sec. Mass Engine: 631 kg (1,391 lb). Diameter: 1.30 m (4.20 ft). Chambers: 1. Chamber Pressure: 98.00 bar. Area Ratio: 114.00. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 64.97. Country: Russia. Status: Development ended 1971.

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.

NK-39 used on Rocket Stages

Used on stage: N1F Block V. on launch vehicle: N1F.

Used on stage: N1F Block V. on launch vehicle: N1F Sr.

Used on stage: N1F Block V. on launch vehicle: N1F-L3M.

Bibliography and Further Reading

Data sheets NPO Trud via Dietrich Haeseler.

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