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    Hello Ashish,<br>
    <br>
    You can play around the Line {#} In Surface {#} command for the wake
    region.<br>
    <br>
    Regards,<br>
    Pawel<br>
    <br>
    <div class="moz-cite-prefix">W dniu 2016-07-12 o 21:57, ashish bhole
      pisze:<br>
    </div>
    <blockquote
cite="mid:CAExBfEJsxkUtfCinUa1icyYFqBLKhMC5_VW9HuJLTJ5bXbC86Q@mail.gmail.com"
      type="cite">
      <div dir="ltr">
        <div>
          <div>
            <div>Hello Guillaume,<br>
              <br>
            </div>
            Thank you so much for you help.<br>
            <br>
          </div>
          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.<br>
          <br>
        </div>
        <div>-- With Regards<br>
        </div>
        <div>Ashish<br>
        </div>
        <div>
          <div>
            <div>
              <div> <br>
                <br>
                <br>
              </div>
            </div>
          </div>
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      <div class="gmail_extra"><br>
        <div class="gmail_quote">On Tue, Jul 12, 2016 at 12:36 PM,
          DILASSER Guillaume <span dir="ltr"><<a
              moz-do-not-send="true"
              href="mailto:Guillaume.DILASSER@cea.fr" target="_blank">Guillaume.DILASSER@cea.fr</a>></span>
          wrote:<br>
          <blockquote class="gmail_quote" style="margin:0 0 0
            .8ex;border-left:1px #ccc solid;padding-left:1ex">
            <div link="blue" vlink="purple" lang="FR">
              <div>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US">Hello Ashish,</span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US"> </span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US">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.</span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US"> </span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US">Sincerely Yours,</span></p>
                <p class="MsoNormal"><span
                    style="font-size:11.0pt;font-family:"Calibri",sans-serif"> </span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Tahoma",sans-serif;color:#000099">Guillaume
                    DILASSER</span><span
style="font-size:10.0pt;font-family:"Tahoma",sans-serif;color:#000099"></span></p>
                <p class="MsoNormal"><span
style="font-size:7.5pt;font-family:"Arial",sans-serif;color:#000099">Doctorant
                    SACM / LEAS</span></p>
                <p class="MsoNormal"><span
style="font-size:7.5pt;font-family:"Arial",sans-serif;color:#000099">CEA
                    - Centre de Saclay - Bât.123 - PC 319c</span><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#000099"></span></p>
                <p class="MsoNormal"><span
style="font-size:7.5pt;font-family:"Arial",sans-serif;color:#000099">91191
                    Gif sur Yvette Cedex - France -</span><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#000099"></span></p>
                <p class="MsoNormal"><span
style="font-size:7.5pt;font-family:"Arial",sans-serif;color:#000099"> </span></p>
                <p class="MsoNormal"><span
style="font-size:7.5pt;font-family:"Arial",sans-serif;color:#000099"><a
                      moz-do-not-send="true"
                      href="mailto:guillaume.dilasser@cea.fr"
                      target="_blank">guillaume.dilasser@cea.fr</a></span></p>
                <p class="MsoNormal"><span
                    style="font-size:11.0pt;font-family:"Calibri",sans-serif"> </span></p>
                <p class="MsoNormal"><span
style="font-size:11.0pt;font-family:"Calibri",sans-serif;color:#1f497d"
                    lang="EN-US"> </span></p>
                <p class="MsoNormal"><b><span
                      style="font-size:11.0pt;font-family:"Calibri",sans-serif"
                      lang="EN-US">De :</span></b><span
                    style="font-size:11.0pt;font-family:"Calibri",sans-serif"
                    lang="EN-US"> gmsh [mailto:<a moz-do-not-send="true"
href="mailto:gmsh-bounces@ace20.montefiore.ulg.ac.be" target="_blank">gmsh-bounces@ace20.montefiore.ulg.ac.be</a>]
                    <b>De la part de</b> ashish bhole<br>
                    <b>Envoyé :</b> lundi 11 juillet 2016 19:02<br>
                    <b>À :</b> <a moz-do-not-send="true"
                      href="mailto:gmsh@onelab.info" target="_blank">gmsh@onelab.info</a><br>
                    <b>Objet :</b> [Gmsh] Problem with Boundary Layer
                    around 2D airfoil with sharp trailing edge</span></p>
                <div>
                  <div class="h5">
                    <p class="MsoNormal"><span lang="EN-US"> </span></p>
                    <div>
                      <div>
                        <div>
                          <div>
                            <div>
                              <div>
                                <p class="MsoNormal"
                                  style="margin-bottom:12.0pt"><span
                                    lang="EN-US">Hello All,</span></p>
                              </div>
                              <p class="MsoNormal"
                                style="margin-bottom:12.0pt"><span
                                  lang="EN-US">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.
                                </span></p>
                            </div>
                            <p class="MsoNormal"><span lang="EN-US">Please
                                share idea how can I make it work
                                correctly.</span></p>
                          </div>
                          <p class="MsoNormal"
                            style="margin-bottom:12.0pt"><span
                              lang="EN-US">Thank you.<br>
                              <br>
                              ------------------------------------<br>
                              Mesh.RecombineAll = 1;<br>
                              <br>
                              Li = 50.0; // distance of inflow boundary
                              from origin<br>
                              Lo = 50.0; // distance of outflow boundary
                              from origin<br>
                              <br>
                              n  = 50; // points on upper/lower surface
                              of airfoil used to define airfoil<br>
                                       // These points may not appear in
                              the mesh.<br>
                              <br>
                              lc1 = 10.0;<br>
                              lc2 = 0.05;<br>
                              <br>
                              m = 2*n - 2; // total number of points on
                              airfoil without repetition<br>
                                           // LE and TE points are
                              common to upper/lower surface<br>
                              <br>
                              nle = n; // point number of LE = no. of
                              points on upper surface<br>
                                       // Point(1) is trailing edge<br>
                              <br>
                              // NACA0012 profile<br>
                              // formula taken from </span><a
                              moz-do-not-send="true"
                              href="http://turbmodels.larc.nasa.gov/naca0012_val.html"
                              target="_blank"><span lang="EN-US">http://turbmodels.larc.nasa.gov/naca0012_val.html</span></a><span
                              lang="EN-US"><br>
                              Macro NACA0012<br>
                                 x2 = x * x;<br>
                                 x3 = x * x2;<br>
                                 x4 = x * x3;<br>
                                 y = 0.594689181*(0.298222773*Sqrt(x) <br>
                                     - 0.127125232*x - 0.357907906*x2 +
                              0.291984971*x3 - 0.105174606*x4);<br>
                              Return<br>
                              <br>
                              // put points on upper surface of airfoil<br>
                              For i In {1:n}<br>
                                 theta = Pi * (i-1) / (n-1);<br>
                                 x = 0.5 * (Cos(theta) + 1.0);<br>
                                 Call NACA0012;<br>
                                 Point(i) = {x, y, 0.0, lc2};<br>
                                 xx[i] = x;<br>
                                 yy[i] = y;<br>
                              EndFor<br>
                              <br>
                              // put points on lower surface of airfoil,
                              use upper surface points and reflect<br>
                              For i In {n+1:m}<br>
                                 Point(i) = {xx[2*n-i], -yy[2*n-i], 0.0,
                              lc2};<br>
                              EndFor<br>
                              <br>
                              Spline(1) = {1:n};<br>
                              Spline(2) = {n:m, 1};<br>
                              <br>
                              Point(1000) = {1.0, Li, 0.0,lc1};<br>
                              Point(1001) = {0.0, Li, 0.0,lc1};<br>
                              Point(1002) = {-Li, 0.0, 0.0,lc1};<br>
                              Point(1003) = {0.0, -Li, 0.0,lc1};<br>
                              Point(1004) = {1.0, -Li, 0.0,lc1};<br>
                              <br>
                              Point(1005) = {Lo, 0.0, 0.0,lc1};<br>
                              Point(1006) = {Lo, Li, 0.0,lc1};<br>
                              Point(1007) = {Lo, -Li, 0.0,lc1};<br>
                              <br>
                              Line(5) = {1000, 1001};<br>
                              Circle(6) = {1001, nle, 1002};<br>
                              Circle(7) = {1002, nle, 1003};<br>
                              Line(8) = {1003, 1004};<br>
                              Line(13) = {1005, 1006};<br>
                              Line(14) = {1005, 1007};<br>
                              Line(15) = {1006, 1000};<br>
                              Line(16) = {1007, 1004};<br>
                              <br>
                              Line Loop(1) = {1,2};<br>
                              Line Loop(2) = {5,6,7,8,-16,-14,13,15};<br>
                              <br>
                              Plane Surface(201) = {2,1};<br>
                              <br>
                              /*<br>
                              //Define Boundary Layer<br>
                              Field[1] = BoundaryLayer;<br>
                              Field[1].EdgesList = {1,2};<br>
                              Field[1].NodesList = {1,m};<br>
                              Field[1].hfar = 0.05;<br>
                              Field[1].hwall_n = 0.009;<br>
                              Field[1].thickness = 0.2;<br>
                              Field[1].ratio = 1.1;<br>
                              Field[1].AnisoMax = 10;<br>
                              Field[1].Quads = 1;<br>
                              Field[1].IntersectMetrics = 0;<br>
                              BoundaryLayer Field = 1;<br>
                              */<br>
                              ------------------------------------<br>
                              <br>
                            </span></p>
                        </div>
                        <p class="MsoNormal">-- With Reagrds</p>
                      </div>
                      <p class="MsoNormal">Ashish Bhole  </p>
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          </blockquote>
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      <br>
      <pre wrap="">_______________________________________________
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</pre>
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