This page no longer updated from 31 October 2001. Latest version can be found at Nodong

Used on stages: Taepodong 1-1, Taepodong 1-2. Used on launch vehicles: Taepodong 1. Propellants: Nitric acid/UDMH Thrust(vac): 14,718 kgf. Thrust(vac): 144.00 kN. Isp: 255 sec. Isp (sea level): 232 sec. Burn time: 176 sec. Chambers: 1. Country: Korea North. Status: In Production. First Flight: 1998. Last Flight: 1998. Flown: 5. References: 284 . Comments: Used in North Korean missiles and the Taepodong 1 satellite launcher. Derived from Isayev designs developed for the Scud missiles and SLBM's of the Makeyev bureau. The engine can be run at full or half thrust.
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Last update 12 March 2001.
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© Mark Wade, 2001 .