S-3
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: USAF
Rocketdyne LOx/Kerosene rocket engine. Juno II, Saturn A-2 studies of 1959. First flight 1958.
Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 725 kg (1,598 lb). Chamber Pressure: 39.50 bar. Area Ratio: 8. Thrust to Weight Ratio: 106.713103448276. Coefficient of Thrust vacuum: 1.71921743620711. Coefficient of Thrust sea level: 1.51668579063749.
Related
- Country
- USA
- Launch Vehicles
- Juno II, Saturn A-2
- Propellants
- Lox/Kerosene
- Stages
- Jupiter Cluster, Jupiter (stage)
- Agency
- Rocketdyne