This page no longer updated from 31 October 2001. Latest version can be found at XLR-89-1

B2C/MA-1/MA-2 -

Credit: Boeing / Rocketdyne. 9,398 bytes. 167 x 205 pixels.

Manufacturer Name: MA-1. Government Designation: XLR-89-1. Designer: Rocketdyne. Developed in: 1956. Application: Atlas A, B, C. Used on stages: Atlas A. Used on launch vehicles: Atlas A. Propellants: Lox/Kerosene Thrust(vac): 77,366 kgf. Thrust(vac): 758.70 kN. Isp: 282 sec. Isp (sea level): 248 sec. Burn time: 133 sec. Mass Engine: 725 kg. Diameter: 1.5 m. Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.71. Country: USA. Status: Out of Production. First Flight: 1957. Last Flight: 1958. Flown: 10. Comments: Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines.
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Last update 12 March 2001.
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