Help with Boundary conditions for simulating flow inside a solid rocket motor
 

Hello gentlemen,
I am tasked with simulating the compressible internal flow of solid rocket motor in openFoam,
After digging around,I was able to find an appropriate set of boundary conditions with gas injection normal to the grain as per the Taylor Culick flow approximation,Pressure outlet at the end of the CD nozzle and symmetry and wall conditions for the rest of the patches.
But I am having trouble finding an appropriate way to specify the values of T,U and P
I have data for chamber stagnation pressure,temperature,mass flow rate,average density of hot gases and thermodynamic parameters like R ,Cp,Cv.I am performing a laminar study with small time steps as seen in the literature.


any help with with setting boundary conditions will be highly appreciated.
Thank you

Have a look at Chapter 16 of [1] and tutorial examples of rhoSimpleFoam.

[1]: 2. Moukalled, Manga and Darwish, The finite volume method in computational fluid dynamics, Springer 2015 , http://www.springer.com/gp/book/9783319168739

Thanks mate, I'll check it out!