3D airfoil boundry conditions
hi,
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 |
3D airfoil simulation..
cancelled.. thanx..
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