The project is actually a study on hypersonic inlets. I've created the geometry in Ansys design modeller and meshing using block mesh strategy in ICEM CFD. Eventhough the quality of mesh is good for fluent, i face some divergence issue while calculation.The model is a simple,single ramp geometry with cowl and the flow is of laminar type( the author actually assumed the flow to be laminar in his experimental setup, Re=1.1*10^6.
The boundary conditions are......
Inlet-------pressure-far-field(gauge pressure=250Pa and mach no=7.9)
Farfield----pressure -far-field(gauge pressure=250Pa and mach no=7.9).
I'm attaching the mesh file of my problem with this...
Hi,
I have gone through your attached case file.
*In fluent, pressure far-field is an inlet boundary type. So it is not wise to use it as you have used in your case.
*Also there must be an outlet boundary. Or you can change your far-field boundary type to symmetry type.
*You said that the flow is laminar. Then why choose SA Model?
*You can reduce the courant number to one for some initial iterations and if necessary you can reduce the URFs to acceptable limits for some initial iterations and then increase it to 1 to avoid divergence, since your case is steady.
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