NK-15

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

NK-15

NK15 engine
NK-15 / 11D51 rocket engine for first stage of N1
Credit: © Mark Wade

Kuznetsov LOx/Kerosene rocket engine. N-1 stage 1 (block A). Development ended 1964. 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. First flight 1969.

AKA: 11D51. Status: Development ended 1964. Date: 1962-72. Number: 120 . Thrust: 1,544.00 kN (347,105 lbf). Unfuelled mass: 1,247 kg (2,749 lb). Specific impulse: 318 s. Specific impulse sea level: 297 s. Height: 2.70 m (8.80 ft). Diameter: 1.50 m (4.90 ft).

Thrust (sl): 1,526.000 kN (343,058 lbf). Thrust (sl): 154,000 kgf. Engine: 1,247 kg (2,749 lb). Chamber Pressure: 78.50 bar. Thrust to Weight Ratio: 126.22. Oxidizer to Fuel Ratio: 2.52.

Subtopics

NK-15V Kuznetsov LOx/Kerosene rocket engine. Development ended 1964. Developed from the NK-9. 8 engines, featuring high-expansion nozzles, used on N1 Stage 2. First flight 1969.

11D51F Kuznetsov LOx/Kerosene rocket engine. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased.

11D51M Kuznetsov LOx/Kerosene rocket engine. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 metric tons thrust to 250 metric tons.

11D52F Kuznetsov LOx/Kerosene rocket engine. N1F 1965 - B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t.

11D52M Kuznetsov LOx/Kerosene rocket engine. N1M 1965 - B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 metric tons per engine.

NK-15VM Kuznetsov LOx/LH2 rocket engine. N-1 stage 2 (block B) replacement. Design 1972. Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests.

NK-43 Kuznetsov LOx/Kerosene rocket engine. N-1F stage 2 (Block B), Kistler stage 2. Development completed 1975. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler.

NK-33 Kuznetsov LOx/Kerosene rocket engine. N-1F stage 1 (block A), Kistler stage 1, Taurus II stage 1. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus.

NK-15F Kuznetsov LOx/Kerosene rocket engine. Development 1966-1972. Engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug on the first stage of a studied N1 variant.

NK-35 Kuznetsov LOx/LH2 rocket engine. Design 1972. Derivative of the NK-15 with kerosene replaced by hydrogen. The engine was canceled before hot-tests. Proposed for the UR-700M Mars booster in 1972, but this was not approved either.

Country: Russia. Launch Vehicles: N1 1964, N1 Nuclear A, N1 Nuclear V-B, N1 Nuclear AF, N1 Nuclear V, N1 1962, N-IUV-III, N-IU, N1M, N1, N1 1969. Propellants: Lox/Kerosene. Stages: N1 Block A, N1 1962 - A, N1 1964 - A, N1U 1965 - A. Agency: Kuznetsov bureau.

Photo Gallery

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z