XLR89-1
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. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. First flight 1957.
Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,038 kgf. Engine: 725 kg (1,598 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 106.712413793104. Coefficient of Thrust vacuum: 1.73020768652599. Coefficient of Thrust sea level: 1.53020768652599.
Related
- Country
- USA
- Launch Vehicles
- Atlas A
- Propellants
- Lox/Kerosene
- Stages
- Atlas A stage
- Agency
- Rocketdyne