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