P8E-9

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P8E-9

P8E-9
Credit: Boeing / Rocketdyne

Rocketdyne Nitric acid/UDMH rocket engine. Lance Booster and Sustainer System. Pressure-fed. Sustainer 4400 -14,400 lbf, 227 sec Isp. Thrust and specific impulse values are at sea level. First flight 1972.

AKA: P8E. Date: 1964. Thrust: 205.44 kN (46,185 lbf). Specific impulse: 238 s. Specific impulse sea level: 238 s.

Thrust (sl): 205.440 kN (46,185 lbf). Thrust (sl): 20,950 kgf. Propellant Formulation: IRFNA/UDMH.

Family: Storable liquid. Country: USA. Propellants: Nitric acid/UDMH. Agency: Rocketdyne.

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