BC in wake cut of airfoil flow
Hello~ I want to solve the aifoil flow using incompressible NS code. Grid is C-type. I don't know exact boundary condition in wake cut region. In fact I set the velocity same in common region .But in the results there is discontinuous pressure field. How can I solve this problem? Do I have to set pressure to fix ?? If you know reference about this problem, please let me know.
Thanks in advance. Best regards.
hai.. i also has same problem with u.. do u fix the problem? hope u can help me.. :confused:
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