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
ClF3/Kerosene
ClF3/Kerosene propellant. No engines reached the operational stage using this propellant combination; chlorine trifluoride had better performance using hydrazine fuel. Rocket propellant kerosene RP-1 was a straight-run kerosene fraction.

Specific impulse: 301 s. Specific impulse sea level: 258 s. Location: 1575.

Optimum Oxidizer to Fuel Ratio: 3.26. Temperature of Combustion: 3,505 deg K. Density: 1.41 g/cc. Characteristic velocity c: 1,575 m/s (5,167 ft/sec). Isp Shifting: 258 sec. Isp Frozen: 250 sec. Oxidizer Density: 1.830 g/cc. Oxidizer Freezing Point: -76 deg C. Oxidizer Boiling Point: 12 deg C. Fuel Density: 0.806 g/cc. Fuel Freezing Point: -73 deg C. Fuel Boiling Point: 147 deg C.

Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use