|January 25, 2006, 09:20||
3D airfoil boundry conditions
i am doing a 3D airfoil simulation for abt a mach no. of 0.2 ... the grid is created .... the entry region is a hemisphere and the exit is shaped in the form of a cylinder... THIS IS FOR 0 ANGLE OF ATTACK. ...
inlet region has tetrahedral elements whereas exit one has hexahedral elements ... and so a default wall is created in between...
during simulation, I setup the interface = symmetry,, and farfield = symmetry , outlet as pressure-outlet and inlet as velocity inlet ....
neone please help me through this. .. when I iterate its diverging ... some temp/pressure AMG solver problemmmm....
OR PLEASE TELL ME THE BOUNDARY CONDITIONS YOU HAVE APPLIED ... if neone has done this earlier....
thanx a lot for reading, sarat
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