XLR-105-5

MA-3
Credit - Boeing / Rocketdyne

Manufacturer Name: MA-2. Government Designation: XLR105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas D. Propellants: Lox/Kerosene. Thrust(vac): 363.200 kN (81,651 lbf). Thrust(sl): 252.700 kN (56,809 lbf). Isp: 309 sec. Isp (sea level): 215 sec. Burn time: 335 sec. Mass Engine: 460 kg (1,010 lb). Diameter: 3.05 m (10.00 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Thrust to Weight Ratio: 80.52. Country: USA. First Flight: 1958. Last Flight: 1967. Flown: 172.

Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines.

XLR-105-5 used on Rocket Stages

Used on stage: Atlas Able. on launch vehicle: Atlas Able.

Used on stage: Atlas Agena LV-3A. on launch vehicle: Atlas LV-3A / Agena A.

Used on stage: Atlas B. on launch vehicle: Atlas B.

Used on stage: Atlas B. on launch vehicle: Atlas C.

Used on stage: Atlas Centaur LV-3C. on launch vehicle: Atlas Centaur LV-3C.

Used on stage: Atlas D. on launch vehicle: Atlas D.

Used on stage: Atlas D. on launch vehicle: Atlas LV-3B / Mercury.

Contact us with any corrections, additions, or comments.

Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z