J-2T-250K

Advanced Engines
Credit - © Mark Wade

Designer: Rocketdyne. Propellants: Lox/LH2. Thrust(vac): 1,111.600 kN (249,898 lbf). Thrust(sl): 731.000 kN (164,335 lbf). Isp: 441 sec. Isp (sea level): 290 sec. Burn time: 348 sec. Diameter: 2.97 m (9.74 ft). Length: 1.25 m (4.10 ft). Chambers: 1. Country: USA. Status: Study 1967.

Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2.

J-2T-250K used on Rocket Stages

Used on stage: Saturn MS-II-1-J-2T-250K. on launch vehicle: Saturn MLV-V-1/J-2T/250K.

Used on stage: Saturn MS-II-1-J-2T-250K. on launch vehicle: Saturn MLV-V-4(S)-B.

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

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