Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
H2O2/UDMH
H2O2/UDMH propellant. Hydrogen peroxide is used as both an oxidizer and a monopropellant. Relatively high density and non-toxic, it was abandoned after early use in British rockets. It was proposed for use with Unsymmetrical Dimethylhydrazine, the storable liquid fuel of choice by the mid-1950's. Having no advantage over the usual oxidizer used with UDMH, N2O4, it did not find application in any production engines.

Specific impulse: 325 s. Specific impulse sea level: 278 s. Location: 1705.

Propellant Formulation: H2O2-98%/UDMH. Optimum Oxidizer to Fuel Ratio: 4.36. Temperature of Combustion: 2,980 deg K. Ratio of Specific Heats: 1.21. Density: 1.25 g/cc. Characteristic velocity c: 1,705 m/s (5,593 ft/sec). Isp Shifting: 281 sec. Isp Frozen: 275 sec. Mol: 21.00 M (68.00 ft). Propellant Formulation: H2O2-95%/UDMH. Optimum Oxidizer to Fuel Ratio: 4.54. Temperature of Combustion: 2,920 deg K. Density: 1.24 g/cc.

Oxidizer Density: 1.440 g/cc. Oxidizer Freezing Point: -1 deg C. Oxidizer Boiling Point: 150 deg C. Fuel Density: 0.793 g/cc. Fuel Freezing Point: -57 deg C. Point: -57 deg C. Fuel Boiling Point: 63 deg C.





Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use