H-1b
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Rocketdyne LOx/Kerosene rocket engine. First flight 1966.
Thrust (sl): 911.900 kN (205,003 lbf). Thrust (sl): 92,986 kgf. Engine: 988 kg (2,178 lb). Chamber Pressure: 48.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 106.329200404858. Coefficient of Thrust vacuum: 1.57681378520837. Coefficient of Thrust sea level: 1.4101471185417.
Related
- Country
- USA
- Launch Vehicles
- Saturn B-1, Saturn A-2, Saturn IB, Saturn IB-C, Saturn IB-CE, Saturn IB-D, Saturn INT-11, Saturn INT-12, Saturn INT-13, Saturn INT-14, Saturn INT-15
- Propellants
- Lox/Kerosene
- Agency
- Rocketdyne