Engine Model: L-5.25H. Propellants: Lox/LH2. Thrust(vac): 27,350.000 kN (6,148,520 lbf). Isp: 410 sec. Isp (sea level): 350 sec. Burn time: 190 sec. Chambers: 1. Country: USA. Status: Study 1963. Engines for recoverable booster engine package 'half stage' of a 1 1/2 stage arrangement. Separation at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange.
L-5.25H used on Rocket Stages