RocketCEA Wraps The NASA Fortran CEA Code And Provides Some Useful Tools¶
See the Code at: https://github.com/sonofeft/RocketCEA
See the Docs at: http://rocketcea.readthedocs.org/en/latest/
See PyPI page at:https://pypi.python.org/pypi/rocketcea
See NASA CEA HomePage at: https://www1.grc.nasa.gov/research-and-engineering/ceaweb/
See NASA CEA On-Line at: https://cearun.grc.nasa.gov/
RocketCEA makes direct calls to the NASA FORTRAN CEA code in “rocket” mode to calculate Isp, Cstar, Tcham etc. and provides tools to help determine useful mixture ratio range, optimum MR and more.
RocketCEA does not use the FORTRAN CEA2.f file directly.
Many modifications have been made in order to wrap CEA with f2py to build a python module.
Additional changes to CEA2.f have been made in order to properly handle hydrazine monopropellant’s ammonia dissociation.
Although the default units in RocketCEA are English units, SI units may be used for both input and output as well. (See Simple Examples > Transport Properties in Docs)
See NASA CEA Documentation: CEA User Manual (NASA RP-1311).pdf and CEA Methodology (NASA RP-1311).pdf
For those interested in using RocketCEA to design rocket thrusters, there are two companion projects RocketIsp and RocketProps.
RocketIsp uses a simplified JANNAF approach to calculate delivered specific impulse (Isp) for liquid rocket thrust chambers.
RocketProps calculates the various liquid propellant properties required to analyse a liquid propellant thrust chamber.
On Windows, 32 bit python 3.8 and above are not supported.
As of this writing (10/5/2021) 64 bit python 3.10 requires Unofficial Binaries to install numpy, scipy and matplotlib.
- Install gfortran
- Standard Examples
- Traditional Example
- Simple Examples
- Finite Area Combustor
- Species Mole Fractions
- Engine Mixture Ratio
- Propellant Selection
- New Propellants
- Plot Examples
- Ambient Isp
- Hydrazine Monopropellant
- Temperature Adjust
- CEA vs TDK vs RPA
- Parasol Example
- RocketCEA Functions