LE-5 Designer: Mitsubishi. Propellants: Lox/LH2. Thrust(vac): 103.000 kN (23,155 lbf). Isp: 450 sec. Burn time: 370 sec. Mass Engine: 245 kg (540 lb). Diameter: 2.49 m (8.16 ft). Length: 2.67 m (8.75 ft). Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 140.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 50.00. Country: Japan. First Flight: 1986. Last Flight: 1992. Flown: 9.00. LE-5 used on Rocket Stages Used on stage: H-1-2. on launch vehicle: H-1. Bibliography and Further Reading Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...                   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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