Encyclopedia Astronautica

Lox/Alcohol propellant rocket stage. Loaded/empty mass 3,500,000/350,000 kg. Thrust 98,000.00 kN. Vacuum specific impulse 247 seconds. All values estimated.

No Engines: 50.

Status: Study 1952.
Gross mass: 3,500,000 kg (7,700,000 lb).
Unfuelled mass: 350,000 kg (770,000 lb).
Height: 33.00 m (108.00 ft).
Diameter: 11.00 m (36.00 ft).
Span: 23.00 m (75.00 ft).
Thrust: 98,000.00 kN (22,031,000 lbf).
Specific impulse: 247 s.
Specific impulse sea level: 210 s.

More... - Chronology...

Associated Countries
Associated Engines
  • A-10 Thiel Lox/Alcohol rocket engine. 2306.8 kN. Study 1942. Planned for use in A-10. Unique dual-thrust chamber / single nozzle design, which was later shown to be not feasible technically. Isp=247s. More...

Associated Launch Vehicles
  • A9/A10/A11/A12 German orbital launch vehicle. The A12 has been named as the designation for a true orbital launch vehicle, as sketched out at Peenemuende. It would have been a four-stage vehicle consisting of the A9+A10+A11+A12 stages. Caluclation suggest it could have placed 10 tonnes into low earth orbit. More...

Associated Propellants
  • Lox/Alcohol Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Alcohol (C2H5OH) was the fuel used for the German V-2 rocket, and the first derivative rocket engines in the United States, Soviet Union, and China used it as well. Better performance was achieved by increasing the alcohol concentration in the post-war engines. But after better-performance rocket-grade kerosene was developed by Rocketdyne in the REAP program of 1953, use of alcohol was abandoned. More...

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