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

Used on stage: A-10. on launch vehicle: A9/A10.

Used on stage: A-10. on launch vehicle: A9/A10/A11.

Used on stage: A-10. on launch vehicle: A9/A10/A11/A12.

Used on stage: A-11. on launch vehicle: A9/A10/A11.

Used on stage: A-11. on launch vehicle: A9/A10/A11/A12.

Used on stage: A-12. on launch vehicle: A9/A10/A11/A12.

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