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Engine Model: Co-axial turboramjet. Propellants: Air/LH2. Thrust(vac): 250.000 kN (56,200 lbf). Thrust(sl): 750.000 kN (168,600 lbf). Isp: 1,200 sec. Isp (sea level): 3,600 sec. Burn time: 6,565 sec. Chambers: 1. Country: Germany. Status: Study 1985.
Co-axial turboramjet used on Rocket Stages
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