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Engine Model: 11D51F. Government Designation: 11D51F. Designer: Kuznetsov. Developed in: 1965. Application: N1F 1965 - A. Propellants: Lox/Kerosene. Thrust(vac): 1,918.000 kN (431,183 lbf). Isp: 331 sec. Isp (sea level): 296 sec. Chambers: 1. Country: Russia. Status: Study 1965.

As described in N1 improvement study, 1965. Block A engine thrust increased.

Engine Model: 11D51M. Government Designation: 11D51M. Designer: Kuznetsov. Developed in: 1965. Application: N1M 1965 - A. Propellants: Lox/Kerosene. Thrust(vac): 2,843.000 kN (639,131 lbf). Isp: 346 sec. Chambers: 1. Country: Russia. Status: Study 1965.

As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes.

Engine Model: 11D52F. Government Designation: 11D52F. Designer: Kuznetsov. Developed in: 1965. Application: N1F 1965 - B. Propellants: Lox/Kerosene. Thrust(vac): 1,961.000 kN (440,850 lbf). Isp: 347 sec. Chambers: 1. Country: Russia. Status: Study 1965.

As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t.

Engine Model: 11D52M. Government Designation: 11D52M. Designer: Kuznetsov. Developed in: 1965. Application: N1M 1965 - B. Propellants: Lox/Kerosene. Thrust(vac): 2,745.000 kN (617,100 lbf). Isp: 330 sec. Isp (sea level): 296 sec. Chambers: 1. Country: Russia. Status: Study 1965.

As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine.

Engine Model: NK-15. 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.

Engine Model: NK-15F. Manufacturer Name: NK-15F. Designer: Kuznetsov. Application: N-1 variant stage 1 (block A). Propellants: Lox/Kerosene. Thrust(vac): 2,180.000 kN (490,080 lbf). Isp: 350 sec. Isp (sea level): 290 sec. Chambers: 1. Country: Russia. Status: Development 1966-1972.

Improved version of NK-15. 24 NK-15F to be used on the Block A (Stage 1) of a studied variant of N-1. That engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug.

Engine Model: NK-15V. Manufacturer Name: NK-15V. Government Designation: 11D52V. Designer: Kuznetsov. Developed in: 1962-72. Application: N-1 stage 2 (block B). Propellants: Lox/Kerosene. Thrust(vac): 1,648.000 kN (370,485 lbf). Isp: 325 sec. Mass Engine: 1,345 kg (2,965 lb). Diameter: 2.00 m (6.50 ft). Length: 2.34 m (7.67 ft). Chambers: 1. Chamber Pressure: 78.50 bar. Oxidizer to Fuel Ratio: 2.52. Thrust to Weight Ratio: 124.90. Country: Russia. Status: Development ended 1964. First Flight: 1969. Last Flight: 1972. Flown: 32.

On the basis of the NK-9 the NK-15V was developed for the N-1 launcher. 8 NK-15V engines, featuring high-expansion nozzles, were used on the Block B (stage 2).

Engine Model: NK-15VM. Manufacturer Name: NK-15VM. Government Designation: 11D52VM. Other Designations: NK-35. Designer: Kuznetsov. Developed in: 1965. Application: N-1 stage 2 (block B) replacement. Propellants: Lox/LH2. Thrust(vac): 1,960.000 kN (440,620 lbf). Chambers: 1. Country: Russia. Status: Design 1972.

Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests. Intended for cryogenic second stage of N-IFV-II,III or N-IMV-II,III launcher versions studied in 1965.

NK-15 used on Rocket Stages
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