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January 25, 2006, 09:20
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3D airfoil boundry conditions
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#1 |
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Guest
Posts: n/a
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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 |
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July 15, 2009, 09:09
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3D airfoil simulation..
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#2 |
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New Member
Chih Fang
Join Date: Jul 2009
Posts: 18
Rep Power: 17  |
cancelled.. thanx..
Last edited by cfang; July 20, 2009 at 23:27. |
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