Draft:NK-9
Soviet rocket engine design
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The NK-9 was a rocket engine designed and built in 1959 by the Kuznetsov Design Bureau. The NK designation was derived from the initials of chief designer Nikolay Kuznetsov. It was intended for the R-9 Desna, but lost this bid to the RD-111. It was then intended for the cruising stage of the Global Rocket 1, but that project was cancelled. The engine was developed into the NK-9V, with a higher expansion ratio, which was also cancelled. It was later developed into the NK-15 for the N1.[2]
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| Country of origin | Soviet Union |
|---|---|
| Date | 1959 |
| Designer | Kuznetsov Design Bureau |
| Application | 1st/2nd-stage engine |
| Successor | NK-15 |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Staged combustion |
| Pumps | Turbopump |
| Performance | |
| Thrust, vacuum | 441 kN (99,000 lbf) |
| Thrust, sea-level | 360 kN (81,000 lbf) |
| Specific impulse, vacuum | 327 s (3.21 km/s) |
| Specific impulse, sea-level | 280 s (2.7 km/s) |
| References | |
| References | [1] |

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