Encyclopedia Astronautica
G-38 Navaho Booster

Navaho G-38 Engine
Navaho G-38 3 Engine Cluster
Lox/Kerosene propellant rocket stage. Loaded/empty mass 76,870/16,780 kg. Thrust 2,048.16 kN. Vacuum specific impulse 282 seconds. Burns out at altitude 21,600 m, Mach 3. Empty Mass estimated.

Cost $ : 12.000 million. No Engines: 3.

AKA: XB-64A; XSM-64A.
Status: Development ended 1958.
Gross mass: 76,870 kg (169,460 lb).
Unfuelled mass: 16,780 kg (36,990 lb).
Height: 27.43 m (89.99 ft).
Diameter: 2.37 m (7.77 ft).
Span: 2.37 m (7.77 ft).
Thrust: 2,048.16 kN (460,444 lbf).
Specific impulse: 282 s.
Specific impulse sea level: 248 s.
Burn time: 90 s.
Number: 8 .

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Associated Countries
Associated Engines
  • LR83-NA-1 Rocketdyne Lox/Kerosene rocket engine. 683 kN. Development ended 1958. Isp=282s. Planned production version of the engine for the booster of the Navaho G-38 intercontinental cruise missile. More...

Associated Launch Vehicles
  • Navaho G-38 American intercontinental cruise missile. The intercontinental-range Navaho G-38 was the ultimate development of the German A-9/A-10 concept. At the time the Navaho program was cancelled on 13 July 1957 missiles were in fabrication with first flight test planned by the end of 1958. More...

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...

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