A-10 engine

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

A-10 engine

Part of A-10

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.

AKA: A-10. Status: Study 1942. Thrust: 2,306.80 kN (518,589 lbf). Specific impulse: 247 s. Specific impulse sea level: 210 s. Burn time: 55 s. Diameter: 4.12 m (13.51 ft).

Thrust (sl): 1,961.300 kN (200,000 kgf / 440,918 lbf).

Country: Germany. Launch Vehicles: A9/A10, A9/A10/A11. Propellants: Lox/Alcohol. Stages: A-10, A-11, A-12. Agency: Thiel.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z