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Hot Fire Test 72Hot Fire Test 72 - Hot firing test of Atlas rocket engine.

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Manufacturer Name: MA-5A. Designer: Rocketdyne. Developed in: 1988. Application: . Used on stages: Atlas MA-5A, Atlas MA-5AS. Used on launch vehicles: Atlas II, Atlas IIA, Atlas IIAS. Propellants: Lox/Kerosene Thrust(vac): 106,750 kgf. Thrust(vac): 1,046.80 kN. Isp: 299 sec. Isp (sea level): 263 sec. Burn time: 172 sec. Mass Engine: 805 kg. Diameter: 2.5 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 132.30. Country: USA. Status: In Production. First Flight: 1991. Last Flight: 1999. Flown: 82. Comments: Designed for booster applications. Gas generator, pump-fed.
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