Engine Model: A-10. Designer: Thiel. Propellants: Lox/Alcohol. Thrust(vac): 2,306.800 kN (518,589 lbf). Thrust(sl): 1,961.300 kN (440,918 lbf). Isp: 247 sec. Isp (sea level): 210 sec. Burn time: 55 sec. Diameter: 4.12 m (13.51 ft). Chambers: 1. Country: Germany. Status: Study 1942. Planned for use in A-10. Unique dual-thrust chamber / single nozzle design, which was later shown to be not feasible technically.
A-10 used on Rocket Stages