MB-3-3
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. License built in Japan for H-1. First flight 1964.
Thrust (sl): 756.100 kN (169,978 lbf). Thrust (sl): 77,104 kgf. Engine: 723 kg (1,593 lb). Chamber Pressure: 39.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 122.240663900415. Coefficient of Thrust vacuum: 1.55303875500592. Coefficient of Thrust sea level: 1.35791680378641.
Related
- Country
- USA
- Launch Vehicles
- Thor SLV-2A Agena D, Thor SLV-2A Agena B, Thor Delta D, Thor Delta E, Thor Delta G, Thor Delta J, Thor Delta N, Thor Delta M, Thorad SLV-2H Agena D, Thor Delta L, Delta 0100, H-1
- Propellants
- Lox/Kerosene
- Stages
- Delta Thor TA, Delta Thor LT, H-1-1
- Agency
- Rocketdyne