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TR-201
TRW N2O4/Aerozine-50 rocket engine. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. First flight 1972.

Number: 90 . Thrust: 41.90 kN (9,419 lbf). Unfuelled mass: 113 kg (249 lb). Specific impulse: 301 s. Burn time: 322 s. Height: 2.27 m (7.44 ft). Diameter: 1.38 m (4.52 ft).

Engine: 113 kg (249 lb). Chamber Pressure: 7.00 bar. Area Ratio: 46. Thrust to Weight Ratio: 31.4338235294118. Oxidizer to Fuel Ratio: 1.59. Coefficient of Thrust vacuum: 1.45719168532336.

Family: Storable liquid. Country: USA. Spacecraft: Apollo LM. Launch Vehicles: Delta 2000, Delta 3000. Propellants: N2O4/Aerozine-50. Stages: Delta P. Agency: TRW.
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