|
|
- # Cpropep is based on the theory presented by Gordon and McBride
- # in the NASA report RP-1311. You can download a pdf version of
- # this document at http://www.arocket.net/library/
-
- # The thermodynamics data file thermo.dat coma also from McBride
- # at the NASA Gleen Research center.
-
- # Here is an example of an input file to be use by cpropep.
- # Any line beginning by a '#' a space or a new_line is considered
- # as a comment.
-
- # This file should first contain a section named 'Propellant' which
- # contain a list of all substance contain in the propellant. The
- # number refer to an element in the data file containing propellant
- # information. In order to have a list of the substance, you could
- # invoque the program like that: 'cpropep -p'
-
- # There is two units that are support for ingredient quantity g (gram) or m (mole)
-
- Propellant
- +600 6.2012 m
- +618 7.7632 m
-
- #Propellant HTPB/KClO4/Al
- #+108 78 g
- #+788 11 g
- #+34 7 g
- #+788 8.4 g
- #+108 62 g
- #+493 18 g
-
- #Propellant DEXTROSE/KNO3
- #+1024 35 g
- #+765 65 g
-
- #Propellant DEXTROSE/KNO3/AL
- #+1024 10 g
- #+765 37 g
- #+34 20 g
-
- #Propellant PVC/AIR
- #+1030 60 g
- #+15 300 g
-
- #Propellant H2O2/OCTANE
- #+673 12 g
- #+469 80 g
-
- #Propellant O2/OCTANE
- #+686 51 g
- #+673 20 g
-
- #Propellant O2/PROPANE
- #+686 51 g
- #+771 20 g
-
- #Propellant O2/NH3
- #+686 28 g
- #+54 20 g
-
- #Propellant NITRIC ACID/OCTANE
- #+630 80 g
- #+673 19 g
-
- # You could then specify a list of problem to be solve. There is 4
- # possible cases:
-
- # TP for temperature-pressure fixed problem
- # You have to specify the temperature and the pressure (of course)
- # There is 4 pressure units (psi, kPa, atm and bar) and 3 temperature units (k, c and f)
-
- #TP
- #+chamber_pressure 500 psi
- #+chamber_temperature 673 k
-
- # HP for enthalpy-pressure fixed problem. It use the enthalpy of
- # the propellant describe at the beginning.
-
- # Only the chamber pressure shoud be specified. The temperature of
- # the product will be the adiabatic flame temperature.
-
- #HP
- #+chamber_pressure 20.4 atm # 136 atm
-
- # FR is used to compute frozen performance.
- # You have to specify the chamber pressure and an exit condition.
- # This condition could be one of the following three:
-
- # exit_pressure: pressure at the exit.
- # supersonic_area_ratio: exit to throat area for an area after the nozzle
- # subsonic_area_ratio: exit to throat area for an area before any nozzle
-
- FR
- +chamber_pressure 68.049 atm
- +exit_pressure 1 atm
- #+supersonic_area_ratio 8.566
- #+subsonic_area_ratio 5
-
- # EQ is used to compute shifting equilibrium performance.
- # The options are the same as for frozen.
-
- EQ
- +chamber_pressure 68.049 atm
- +exit_pressure 1 atm
- #+supersonic_area_ratio 10
- #+subsonic_area_ratio 5
|