| HP-1 |
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Engine Model: HP-1. Propellants: Lox/LH2. Thrust(vac): 6,536.000 kN (1,469,351 lbf). Isp: 451 sec. Isp (sea level): 379 sec. Burn time: 386 sec. Chambers: 1. Country: USA. Status: Study 1963. Operational date would have been December 1974. HP-1 used on Rocket Stages
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