LE-5A Other Designations: LE-5EC. Designer: Mitsubishi. Propellants: Lox/LH2. Thrust(vac): 121.500 kN (27,314 lbf). Isp: 452 sec. Burn time: 609 sec. Mass Engine: 242 kg (533 lb). Diameter: 4.00 m (13.10 ft). Length: 2.67 m (8.75 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 130.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 51.20. Country: Japan. First Flight: 1994. Last Flight: 1999. Flown: 7.00. LE-5A used on Rocket Stages Used on stage: H-2-2. on launch vehicle: H-2.                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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