Encyclopedia Astronautica

Navaho G-38 Engine
Navaho G-38 3 Engine Cluster
Credit: Boeing / Rocketdyne
Navaho G-38 Engine
Navaho G-38 Engine Section
Credit: Tom Johnson
Rocketdyne Lox/Kerosene rocket engine. 602 kN. Out of production. Isp=273s. Experimental version of the engine for the booster of the Navaho G-38 intercontinental cruise missile. Flown in the Navaho G-26 booster prototypes. First flight 1956.

Used guide vanes for thrust vectoring. Gas generator, pump-fed.

Thrust (sl): 533.700 kN (119,981 lbf). Thrust (sl): 54,422 kgf. Propellant Formulation: Lox/JP-4 or RP-1.

Status: Out of production.
Diameter: 0.88 m (2.88 ft).
Thrust: 602.00 kN (135,334 lbf).
Specific impulse: 273 s.
Specific impulse sea level: 242 s.
Burn time: 76 s.
First Launch: 1954.
Number: 22 .

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Associated Countries
See also
Associated Launch Vehicles
  • Navaho G-26 American intermediate range cruise missile. The Navaho G-26 was a 2/3 scale test version of the operational Navaho G-38. The Navaho program was cancelled on 13 July 1957, but already-built G-26 test missiles were flown to the end of 1958. More...

Associated Manufacturers and Agencies
Associated Propellants
  • Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

Associated Stages
  • G-26 Booster Lox/Alcohol propellant rocket stage. Loaded/empty mass 42,403/11,337 kg. Thrust 1,204.12 kN. Vacuum specific impulse 273 seconds. Burns out at altitude 13,000 m, Mach 3 More...

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