tetroxide (NTO or ) Used in three first stages of the Russian Proton booster, Indian Vikas engine for PSLV and GSLV rockets, most Chinese boosters, a number of military, orbital and deep space rockets, as this fuel combination is hypergolic and storable for long periods at reasonable temperatures and pressures. Hydrazine () Used in deep space missions because it is storable and hypergolic, and can be used as a monopropellant with a catalyst. Aerozine-50 (50/50 hydrazine and UDMH) Used in deep space missions because it is storable and hypergolic, and can be used as a monopropellant with a catalyst. Table The table uses data from the JANNAF thermochemical tables (Joint Army-Navy-NASA-Air Force (JANNAF) Interagency Propulsion Committee) throughout, with best-possible specific impulse calculated by Rocketdyne under the assumptions of adiabatic combustion, isentropic expansion, one-dimensional expansion and shifting equilibrium. Some units have been converted to metric, but pressures have not. Definitions Ve Average exhaust velocity, m/s. The same measure as specific impulse in different units, numerically equal to specific impulse in N·s/kg. r Mixture ratio: mass oxidizer / mass fuel Tc Chamber temperature, °C d Bulk density of fuel and oxidizer, g/cm3 C* Characteristic velocity, m/s. Equal to chamber pressure multiplied by throat area, divided by mass flow rate. Used to check experimental rocket's combustion efficiency. Bipropellants Definitions of some of the mixtures: IRFNA IIIa 83.4% HNO3, 14% NO2, 2% H2O, 0.6% HF IRFNA IV HDA 54.3% HNO3, 44% NO2, 1% H2O, 0.7% HF RP-1 See MIL-P-25576C, basically kerosene (approximately ) MMH monomethylhydrazine Has not all data for CO/O, purposed for NASA for Martian-based rockets, only a specific impulse about 250 s. r Mixture ratio: mass oxidizer / mass fuel Ve Average exhaust velocity, m/s. The same measure as specific impulse in different units, numerically equal to specific impulse in N·s/kg. C* Characteristic velocity, m/s. Equal to chamber pressure multiplied by throat area, divided by mass flow rate. Used to check experimental rocket's combustion efficiency. Tc Chamber temperature, °C d Bulk density of fuel and oxidizer, g/cm3 Monopropellants References External links Cpropep-Web an online computer program to calculate propellant performance in rocket engines Design Tool for Liquid Rocket Engine Thermodynamic Analysis is a computer program to predict the performance of the liquid-propellant rocket engines. for a history of liquid rocket propellants in the US by a pioneering rocket propellant developer. Rocket propulsion Rocket propellants ja:ロケットエンジンの推進剤#液体燃料ロケット