LE-5A
Engine · Japan
Original archive entry. The text, images and links below are kept as they were written.
Mitsubishi LOx/LH2 rocket engine. Used on H-2 launch vehicle. First flight 1994.
Engine: 242 kg (533 lb). Chamber Pressure: 40.00 bar. Area Ratio: 130. Thrust to Weight Ratio: 51.1964958168671. Oxidizer to Fuel Ratio: 5. Coefficient of Thrust vacuum: 1.87986266248807.
Related
- Country
- Japan
- Launch Vehicles
- H-II
- Propellants
- Lox/LH2
- Stages
- LE-5EC
- Agency
- Mitsubishi