H-1 engine
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. First flight 1961. Surplus Saturn motors adapted for use in Delta launch vehicle.
Thrust (sl): 836.200 kN (187,985 lbf). Thrust (sl): 85,275 kgf. Engine: 635 kg (1,399 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 152.196850393701. Oxidizer to Fuel Ratio: 2.23. Coefficient of Thrust vacuum: 1.74073055260789. Coefficient of Thrust sea level: 1.54073055260789.
Related
- Country
- USA
- Launch Vehicles
- Juno V-A, Juno V-B, Saturn A-1, Saturn C-2, Saturn I
- Propellants
- Lox/Kerosene
- Stages
- S-I stage
- Agency
- Rocketdyne
- Bibliography
- 225