A-7 (original) (raw)

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A-7

Part of Model 39a

A-6
A-6 differed from A-7 in having two fuel downcomers, one is hidden on the other side of the engine. The A-7 had one fuel downcomer to the aft manifold for engine cooling.
Credit: Boeing / Rocketdyne

Rocketdyne LOx/Hydyne rocket engine. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level.

Status: Out of Production. Date: 1951. Number: 9 . Thrust: 416.20 kN (93,565 lbf). Unfuelled mass: 658 kg (1,450 lb). Specific impulse: 265 s. Specific impulse sea level: 235 s. Burn time: 155 s. Diameter: 1.77 m (5.80 ft).

Thrust (sl): 369.100 kN (82,977 lbf). Thrust (sl): 37,635 kgf. Engine: 658 kg (1,450 lb). Propellant Formulation: Lox/Alcohol or Hydyne. Thrust to Weight Ratio: 64.2112462006079.

Country: USA. Launch Vehicles: Jupiter C. Propellants: Lox/Hydyne. Stages: Jupiter C stage, Redstone Mercury. Agency: Rocketdyne.

Photo Gallery

	Redstone engineCredit: NASA

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