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XCNLT-1500
Aerojet isopropylnitrate monopropellant rocket engine for Lark missile. Development begun March 1945. Turborocket; turbine-pump fed monopropellant, single uncooled thrust chamber. Development unsuccessful, all work terminated.

AKA: XCNLT-600/1000/1500;XLR15-AJ-1. First Launch: March 1945. Thrust: 6.66 kN (1,497 lbf). Unfuelled mass: 33 kg (72 lb). Burn time: 60 s. Height: 0.52 m (1.70 ft). Diameter: 0.18 m (0.58 ft).

Development begun March 1945. Turborocket (included in general R&D contract). Turbine-pump fed monopropellant, single uncooled thrust chamber. Starting catalyst carried separately. Squib or oxygen spark ignition. Development unsuccessful, all work terminated contract W33-038. Also lower thrust XCNLT-600/1000 models.

Thrust (sl): 6.660 kN (1,497 lbf). Thrust (sl): 680 kgf. Engine: 33 kg (72 lb). Chamber Pressure: 61.00 bar. Propellant Formulation: Nitromethane.



Family: Monopropellant. Country: USA. Propellants: Isopropylnitrate. Agency: Aerojet.

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