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A-10
LOx/Alcohol propellant rocket stage. .

Status: Study 1944. Thrust: 2,306.90 kN (518,611 lbf). Gross mass: 69,043 kg (152,213 lb). Unfuelled mass: 16,993 kg (37,463 lb). Specific impulse: 247 s. Specific impulse sea level: 210 s. Burn time: 55 s. Height: 20.00 m (65.00 ft). Diameter: 4.12 m (13.51 ft). Span: 9.00 m (29.50 ft).

Subtopics

A-10 engine Thiel LOx/Alcohol rocket engine. Study 1942. Planned for use in A-10. Unique dual-thrust chamber / single nozzle design, which was later shown to be not feasible technically.

Country: Germany. Engines: A-10 engine. Launch Vehicles: A9/A10, A9/A10/A11/A12, A9/A10/A11. Propellants: Lox/Alcohol. More at: 9612.

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