MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-200K engines replacing standard J-2 engines in upper stages.

at: 28.0 degrees. Liftoff Thrust: 4,080,890 kgf. Total Mass: 3,216,150 kg. Core Diameter: 10.1 m. Total Length: 89.0 m.

• Stage Number: 1. 1 x Saturn MS-IC-1 Gross Mass: 2,694,703 kg. Empty Mass: 169,719 kg. Thrust (vac): 4,685,469 kgf. Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 48.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1A

• Stage Number: 2. 1 x Saturn MS-II-1-J-2T-200K Gross Mass: 521,447 kg. Empty Mass: 49,877 kg. Thrust (vac): 453,432 kgf. Isp: 435 sec. Burn time: 429 sec. Isp(sl): 300 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 25.9 m. Propellants: Lox/LH2 No Engines: 5. J-2T-200K

• 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm
• 230 - Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.