# BC at airfoil TE

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 July 15, 2002, 09:33 BC at airfoil TE #1 keitee Guest   Posts: n/a Hi everyone. I wish to know how best to set a TE boundary condition for 2D airfoil calculation, when TE has some thickness. Governing EQ is 2D Navier-Stokes. and geometry is C type. Anyone can help me?

 July 15, 2002, 09:48 Re: BC at airfoil TE #2 Li Yang Guest   Posts: n/a Hi, It will be good to insert another block behind the TE. Regards Li

 July 15, 2002, 11:31 Re: BC at airfoil TE #3 kenn Guest   Posts: n/a what does TE represent?

 July 15, 2002, 13:13 Re: BC at airfoil TE #4 Peter Attar Guest   Posts: n/a Trailing Edge

 July 15, 2002, 13:42 Re: BC at airfoil TE #5 Axel Rohde Guest   Posts: n/a If you have a C-grid, you really want a sharp trailing edge, otherwise you are better off with an O-grid. So I would say the quickest way will be to fix your TE, i.e. make the two points defining the blunt edge coincide, which makes it sharp.

 July 15, 2002, 16:39 Re: BC at airfoil TE #6 Li Yang Guest   Posts: n/a I think you are right. It will be the quickest way by using O-grid. Enough grid points can be employed at the trailing edge so that the wake can be captured. However, for this case with a structured grid topology, good quality grid can only be achieved by using multiblock. Regards Li

 July 15, 2002, 17:28 Re: BC at airfoil TE #7 Axel Rohde Guest   Posts: n/a I am not sure about the thickness of this TE, but if it's less than 1% of chord, I would not even bother modeling it. Drag prediction for airfoils, even with a full Navier Stokes solver and the 'right' turbulence model, is a shot in the dark, whereas the TE thickness effect on lift is negligible. If he uses an O-grid, he will have to throw a lot of points on this TE to make it numerically round. Otherwise he will have non-smooth transformation metrics at the 'kink', which will most likely create numerical problems for the solver. My recommendation: stay with the C-grid and make the edge sharp. For a C-grid, a sharp TE does not pose any problem (metrics are perfectly smooth).

 July 23, 2002, 10:54 Re: BC at airfoil TE #8 xxx Guest   Posts: n/a Refer to Jack Moran Computational Fluid Dynamics

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