Liquid monomethylhydrazine (CH
6N
2) and dinitrogen tetroxide (N
2O
4) are burned in the combustion chamber of a rocket engine. The oxidizer to fuel ratio is 2.5 (i.e. in the ratio of 1 mole of CH
6N
2 to 1.2518 moles of N
2O
4).
This application will calculate
- the adiabatic flame temperature and composition of the combustion products (i.e. in the combustion chamber)
- the pressures and temperatures in the throat and exit
- and the theoretical rocket performance, including the ideal specific impulse, characteristic velocity, and sonic velocity.
