[Gmsh] Boundary Layer for airfoil with blunt TE

Thu Aug 29 11:53:43 CEST 2019

Hello gmsh-community,

I'm having trouble creating a high quality mesh for an airfoil with a blunt
TE.
I want to use the boundaryLayer field only up to the TE (see picture
airfoilFull.png).
The problem is at the TE the mesh goes through the edges and I'am getting
open faces if I convert it to openFOAM (see picture airfoilTE.png).

I tried different things:

   1. changing h_wall_n:  Lowering h_wall_n results in  the same behaviour.
   Choosing a high h_wall_n makes even wierder behaviour.
   2. Changing the local refinement around the points on the TE or at
   points or lines close to it -> does not help
   3. I also tried using the fan, but I am not satisfied with the grid
   resolution at the mesh and the resulting skewness around it (see picture
   airfoil_withFan.png)

I am using gmsh 4.2.1
My .geo file is below and is also attatched.

Thank you! Regards

Iason Tsiapkinis

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Point(236) = {0.1711294116,-0.02636567275,0,0.0002919509288};
Point(237) = {0.1721156925,-0.02663896046,0,0.0002919509288};
Point(238) = {0.1730603392,-0.02690058893,0,0.0002919509288};
Point(239) = {0.1739634116,-0.02715058788,0,0.0002919509288};
Point(240) = {0.1748249789,-0.02738898958,0,0.0002919509288};
Point(241) = {0.1756414284,-0.02761480747,0,0.000149970964};
Point(1001) = {0.180594157118+0.001,-0.01722604,0,0.001799970964};
Point(1239) = {0.172158652+0.001,-0.037026971,0,0.001799970964};
Spline(1) =
{121,122,123,124,125,126,127,128,129,130,131,132,133,134,135,136,137,138,139,140,141,142,143,144,145,146,147,148,149,150,151,152,153,154,155,156,157,158,159,160,161,162,163,164,165,166,167,168,169,170,171,172,173,174,175,176,177,178,179,180,181,182,183,184,185,186,187,188,189,190,191,192,193,194,195,196,197,198,199,200,201,202,203,204,205,206,207,208,209,210,211,212,213,214,215,216,217,218,219,220,221,222,223,224,225,226,227,228,229,230,231,232,233,234,235,236,237,238,239,240,241};
//
Spline(2) =
{1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17,18,19,20,21,22,23,24,25,26,27,28,29,30,31,32,33,34,35,36,37,38,39,40,41,42,43,44,45,46,47,48,49,50,51,52,53,54,55,56,57,58,59,60,61,62,63,64,65,66,67,68,69,70,71,72,73,74,75,76,77,78,79,80,81,82,83,84,85,86,87,88,89,90,91,92,93,94,95,96,97,98,99,100,101,102,103,104,105,106,107,108,109,110,111,112,113,114,115,116,117,118,119,120,121};
////
Line(3) = {241, 1};
Line Loop(1000) = {3,2,1};

// flow field boundaries
Point(242) = {1.08,-3.6+3.4200,0,0.01};
Point(243) = {-0.9+4*0.18,-3.6+3.4200,0,0.02};
Point(244) = {-0.9+4*0.18,3.6-3.4200,0,0.02};
Point(245) = {1.08,3.6-3.4200,0,0.01};
Line(12) = {242,243};
Line(13) = {243,244};
Line(14) = {244,245};
Line(15) = {245,242};
Line Loop(1001) = {-15,-14,-13,-12};
Plane Surface(1002) = {1001,1000};

// line for wake refinement
coordChordTop[] = Point{1};
coordChordBottom[] = Point{241};
Point(251) =
{(coordChordBottom[0]+coordChordTop[0])/2,(coordChordBottom[1]+coordChordTop[1])/2,0,0.1799970964};
Point(252) =
{1.079985482,(coordChordBottom[1]+coordChordTop[1])/2,0,0.1799970964};
Line(17) = {251,252};

//Define Boundary Layer
Field[6] = BoundaryLayer;
Field[6].EdgesList = {1,2}; //,3, 1009
Field[6].NodesList = {2,240};
Field[6].FanNodesList = {1,241};
Field[6].hfar = 1e-3;
Field[6].hwall_n = 0.1e-4;
Field[6].thickness = 0.005;
Field[6].ratio = 1.05;
Field[6].AnisoMax = 0.1;
Field[6].Quads = 1;
Field[6].IntersectMetrics = 0;
BoundaryLayer Field = 6;

//Recombine Surface{1,2} = 0;
j1[] = Extrude {0,0,-0.0018} {Surface{1002};Layers{1};Recombine;};
Physical Surface("inlet") = {j1[4]};
Physical Surface("outlet") = {j1[2]};
Physical Surface("topAndBottom") = {j1[3], j1[5]};
Physical Surface("airfoil") = {j1[6],j1[7],1038};
Physical Surface("frontAndBack") = {j1[0],1002};
Physical Volume("Volumen") = {j1[1]};
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