MB-3-1
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. Boosted Delta A, B, C, Thor Able-Star. First flight 1960.
Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.628304821151. Coefficient of Thrust vacuum: 1.39705131752785. Coefficient of Thrust sea level: 1.19705131752785.
Related
- Country
- USA
- Launch Vehicles
- Thor Delta A, Thor Ablestar, Thor Delta B, Delta C
- Propellants
- Lox/Kerosene
- Stages
- Thor DM-21
- Agency
- Rocketdyne