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LE-5A
Part of LE-5 engine
Mitsubishi LOx/LH2 rocket engine. Used on H-2 launch vehicle. First flight 1994.

AKA: LE-5EC. Number: 7 . Thrust: 121.50 kN (27,314 lbf). Unfuelled mass: 242 kg (533 lb). Specific impulse: 452 s. Burn time: 609 s. Height: 2.67 m (8.75 ft). Diameter: 4.00 m (13.10 ft).

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.

Country: Japan. Launch Vehicles: H-II. Propellants: Lox/LH2. Stages: LE-5EC. Agency: Mitsubishi.
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