Hello Ashish,
You can play around the Line {#} In Surface {#} command for the wake region.
Regards,
Pawel
W dniu 2016-07-12 o 21:57, ashish bhole pisze:
Hello Guillaume,
Thank you so much for you help.
Can I extend the same boundary layer into wake region? I tried doing
the same by drawing a line from trailing edge to farfield and creating
boundary layer around it. But I have not succeeded yet.
-- With Regards
Ashish
On Tue, Jul 12, 2016 at 12:36 PM, DILASSER Guillaume
<[email protected] <mailto:[email protected]>> wrote:
Hello Ashish,
You can add to the BoundaryLayer definition the property
“Field[1].FanNodesList = {1,n} ;” to get rid of the weird behavior
of the mesh around the tips of the foil. Somehow, the 2D blossom
recombination algorithm does not like when you do that so replace
it with the standard one using “Mesh.RecombinationAlgorithm = 0
;”. Both modifications are done in the enclosed file. Finally, you
may want to increase the mesh density at the front of the foil to
better match the geometry there.
Sincerely Yours,
Guillaume DILASSER
Doctorant SACM / LEAS
CEA - Centre de Saclay - Bât.123 - PC 319c
91191 Gif sur Yvette Cedex - France -
[email protected] <mailto:[email protected]>
*De :*gmsh [mailto:[email protected]
<mailto:[email protected]>] *De la part de*
ashish bhole
*Envoyé :* lundi 11 juillet 2016 19:02
*À :* [email protected] <mailto:[email protected]>
*Objet :* [Gmsh] Problem with Boundary Layer around 2D airfoil
with sharp trailing edge
Hello All,
I am new at using gmsh. I want to generate a mesh (unstructured)
around 2D airfoil with sharp trailing edge. When I use Boundary
Layer field in gmsh, it generates boundary layer but with
undesirable intersections. I have attached my .geo file here.
Currently, I have commented Boundary Layer field lines in the script.
Please share idea how can I make it work correctly.
Thank you.
------------------------------------
Mesh.RecombineAll = 1;
Li = 50.0; // distance of inflow boundary from origin
Lo = 50.0; // distance of outflow boundary from origin
n = 50; // points on upper/lower surface of airfoil used to
define airfoil
// These points may not appear in the mesh.
lc1 = 10.0;
lc2 = 0.05;
m = 2*n - 2; // total number of points on airfoil without repetition
// LE and TE points are common to upper/lower surface
nle = n; // point number of LE = no. of points on upper surface
// Point(1) is trailing edge
// NACA0012 profile
// formula taken from
http://turbmodels.larc.nasa.gov/naca0012_val.html
Macro NACA0012
x2 = x * x;
x3 = x * x2;
x4 = x * x3;
y = 0.594689181*(0.298222773*Sqrt(x)
- 0.127125232*x - 0.357907906*x2 + 0.291984971*x3 -
0.105174606*x4);
Return
// put points on upper surface of airfoil
For i In {1:n}
theta = Pi * (i-1) / (n-1);
x = 0.5 * (Cos(theta) + 1.0);
Call NACA0012;
Point(i) = {x, y, 0.0, lc2};
xx[i] = x;
yy[i] = y;
EndFor
// put points on lower surface of airfoil, use upper surface
points and reflect
For i In {n+1:m}
Point(i) = {xx[2*n-i], -yy[2*n-i], 0.0, lc2};
EndFor
Spline(1) = {1:n};
Spline(2) = {n:m, 1};
Point(1000) = {1.0, Li, 0.0,lc1};
Point(1001) = {0.0, Li, 0.0,lc1};
Point(1002) = {-Li, 0.0, 0.0,lc1};
Point(1003) = {0.0, -Li, 0.0,lc1};
Point(1004) = {1.0, -Li, 0.0,lc1};
Point(1005) = {Lo, 0.0, 0.0,lc1};
Point(1006) = {Lo, Li, 0.0,lc1};
Point(1007) = {Lo, -Li, 0.0,lc1};
Line(5) = {1000, 1001};
Circle(6) = {1001, nle, 1002};
Circle(7) = {1002, nle, 1003};
Line(8) = {1003, 1004};
Line(13) = {1005, 1006};
Line(14) = {1005, 1007};
Line(15) = {1006, 1000};
Line(16) = {1007, 1004};
Line Loop(1) = {1,2};
Line Loop(2) = {5,6,7,8,-16,-14,13,15};
Plane Surface(201) = {2,1};
/*
//Define Boundary Layer
Field[1] = BoundaryLayer;
Field[1].EdgesList = {1,2};
Field[1].NodesList = {1,m};
Field[1].hfar = 0.05;
Field[1].hwall_n = 0.009;
Field[1].thickness = 0.2;
Field[1].ratio = 1.1;
Field[1].AnisoMax = 10;
Field[1].Quads = 1;
Field[1].IntersectMetrics = 0;
BoundaryLayer Field = 1;
*/
------------------------------------
-- With Reagrds
Ashish Bhole
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