J-2-SL
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Rocketdyne LOx/LH2 rocket engine. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use.
Thrust (sl): 729.300 kN (163,953 lbf). Thrust (sl): 74,366 kgf. Engine: 1,360 kg (2,990 lb). Chamber Pressure: 30.00 bar. Area Ratio: 14. Thrust to Weight Ratio: 74.73.
Related
- Country
- USA
- Launch Vehicles
- Saturn INT-19
- Propellants
- Lox/LH2
- Stages
- Saturn II-SL
- Agency
- Rocketdyne