[Xwang]

Hi to all,
I'm studying openFOAM to use it to calculate aerodynamic coefficients (forces and moments) of complete air-crafts (subsonic, transonic and supersonic studies) and vehicles for steady state simulation.
I want to use only open source programs so I've thought the following procedure:
1) create an stl 3d model using Varkon
2) create a mesh using SnappyHexMesh from the stl model
3) define boundary conditions and solver parameters
4) run the simulation till convergence has been reached
5) check the results using paraview
6) check the results plotting aerodynamic coefficients versus simulation step to be sure that even the coefficients have converged
I have the following questions:
a) Do you agree with such method? Is it feasible
b) I've seen that SnappyHexMesh can be unreliable on sharp edges. Is it better to use a different mesh tool?
c) What kind of solver do you suggest to use considering that initially I would like to learn a pretty general usable solver for all the cases which should be able take in account also the boundary layer around the geometry?
d) How can I compute force and moment coefficients?
e) How can I set up simulation so that it stops calculation when simulation has been reached?
6) How can I plot the graph of point 6?
Thank you for you help,
Xwang