MS-II
 | This article includes a list of references, related reading, or external links, but its sources remain unclear because it lacks inline citations. (April 2013) |
The MS-II was a proposed further development of the S-II rocket stage developed by North American Aviation.
Rocket Specifications
Mass: 521,447 kg (1,149,593 lb)
Empty Mass: 49,877 kg (109,959 lb)
Thrust(vac): 5,165.790 kN (1,161316 lbf)
Isp: 425 sec Burn Time: 361 sec
Propellants: Lox/LH2. Isp(sl): 306 sec
Diameter: 10.06m(33.00ft)
Span: 10.06m(33.00ft)
Length: 25.88m(84.90ft)
Engines: 5x J-2
External links
 | This rocketry article is a stub. You can help Wikipedia by expanding it. |
 | This article about aircraft engines is a stub. You can help Wikipedia by expanding it. |