NK-15

NK15 engine
Credit - © Mark Wade

Manufacturer Name: NK-15. Government Designation: 11D51. Designer: Kuznetsov. Developed in: 1962-72. Application: N-1 stage 1 (block A). Propellants: Lox/Kerosene. Thrust(vac): 1,544.000 kN (347,105 lbf). Thrust(sl): 1,526.000 kN (343,058 lbf). Isp: 318 sec. Isp (sea level): 297 sec. Mass Engine: 1,247 kg (2,749 lb). Diameter: 1.50 m (4.90 ft). Length: 2.70 m (8.80 ft). Chambers: 1. Chamber Pressure: 78.50 bar. Oxidizer to Fuel Ratio: 2.52. Thrust to Weight Ratio: 126.22. Country: Russia. Status: Development ended 1964. First Flight: 1969. Last Flight: 1972. Flown: 120.

On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1.

NK-15 used on Rocket Stages

Used on stage: N1 1962 - A. on launch vehicle: N1 1962.

Used on stage: N1 1962 - A. on launch vehicle: N1 Nuclear A.

Used on stage: N1 1962 - A. on launch vehicle: N1 Nuclear AF.

Used on stage: N1 1962 - A. on launch vehicle: N1 Nuclear V.

Used on stage: N1 1962 - A. on launch vehicle: N1 Nuclear V-B.

Used on stage: N1 1964 - A. on launch vehicle: N1 1964.

Used on stage: N1 Block A. on launch vehicle: N1.

Used on stage: N1 Block A. on launch vehicle: N1M.

Used on stage: N1U 1965 - A. on launch vehicle: N-IU.

Used on stage: N1U 1965 - A. on launch vehicle: N-IUV-III.

Bibliography and Further Reading

Kobelyev, V N; Milovanov, A G, Rakety Nositeli, Moscow State Aviation Techology University, 1993 via Dietrich Haeseler.

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© Mark Wade, 1997 - 2007 except where otherwise noted.

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