This page no longer updated from 31 October 2001. Latest version can be found at LR-8

Designer: Thiokol. Application: Manned rocketplanes. Used on spacecraft: D-558-2, X-1E. Propellants: Lox/Alcohol Mass Engine: 157 kg. Diameter: 0.5 m. Length: 1.5 m. Chambers: 4. Status: Out of Production. Comments: Advanced version of XLR-11 used on X-1E and D-558-II rocketplanes. Could not be throttled, but four combustion chambers could be run individually. 2700 kgf at sea level.
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Last update 12 March 2001.
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© Mark Wade, 2001 .