Nitric acid/JP-X
Propellant
Original archive entry. The text, images and links below are kept as they were written.
Nitric acid/JP-X propellant. The addition of approximately 40 per cent of UDMH to JP-4 resulted in a formulation (JP-X) which solved both the combustion and the ignition difficulties experienced with WFNA/ JP-4 and IRFNA/JP-4.
Optimum Oxidizer to Fuel Ratio: 4.13. Temperature of Combustion: 3,205 deg K. Density: 1.33 g/cc. Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -42 deg C. Oxidizer Boiling Point: 86 deg C. Fuel Density: 0.900 g/cc.
Subtopics
- AJ10-28 Aerojet Nitric acid/JP-X rocket engine. SNORT Sled. Development begun early 1950s. 35,000 lbf thrust, 2-10 second duration. JP-X was a jet fuel / hydrazine mixture.
Related
- Engines
- AJ10-28