This page no longer updated from 31 October 2001. Latest version can be found at RL-50

Designer: Pratt and Whitney. Propellants: Lox/LH2 Thrust(vac): 29,500 kgf. Thrust(vac): 290.00 kN. Isp: 472 sec. Mass Engine: 500 kg. Chambers: 1. Oxidizer to Fuel Ratio: 5.50. Country: USA. Status: Development. References: 427 .

The the RL-50 is an advanced, high-performance upper-stage rocket engine being developed by Pratt & Whitney for both domestic and international launch vehicles. The RL-50 meets future launch vehicle requirements for increased payload delivery capability, improved launch system operability and enhanced system cost effectiveness. It provides more than twice the thrust of existing upper-stage Lox/LH2 engines. The RL-50 is to be available in 2003, and incorporates modern technologies to simplify the engine and decrease costs.

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Last update 12 March 2001.
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© Mark Wade, 2001 .