Engine Model: XLR11. Government Designation: XLR11-RM-1. Designer: Reaction Motors, Thiokol. Application: Manned rocketplanes. Propellants: Lox/Alcohol. Thrust(sl): 26.670 kN (5,996 lbf). Throttled thrust(vac): 680.000 kN (152,870 lbf). Mass Engine: 157 kg (346 lb). Diameter: 0.46 m (1.50 ft). Length: 1.45 m (4.75 ft). Chambers: 4. Country: USA. Status: Out of Production. Rocket engine developed to break the sound barrier and used twenty years later to power experimental lifting bodies. XLR11-RM-1 was nitrogen pressurised; -RM-3 helium pressurised; -RM-5 hydrogen pressurised. Spark plug ignition, regeneratively cooled with alcohol fuel, supplemented by film cooling of chamber. Could not be throttled, but four combustion chambers could be run individually. 2700 kgf total with four chambers at sea level. XF-92 application would have used six chambers. Mass of engine without pump 100 kg.
