![]() ![]() Present work has extended these eminent linear meshing scheme by utilizing subparametric transformation on higher order triangular elements. The accuracy of an eminent linear mesh generator scheme presented by Gilbert Strang and Persson has been proved and verified. m by implementing simple changes based on the present 4-digit NACA0018 airfoil profile. Meshing is executed with the MATLAB code AirfoilHOmesh2d. A NACA0018 airfoil design of 18% thickness of max camber is under consideration for the present work. An itemized extraction of the edge information, nodal coordinates, the total number of discretized elements and the triangle indices has been carried out from the present meshing. Linear, quadratic, cubic, quartic, quintic and sextic order triangle shaped elements are been utilized to discretize the area near the airfoil shape. The subparametric transformation approach has been implemented in the present accurate and efficient meshing. ![]() ![]() An automated meshing has been performed by linear to sextic order (n = 1, 2, 3, 4, 5 and 6) simple triangle elements using MATLAB code. A novel higher order meshing around the airfoil design by using finite simple triangle elements has been presented in this paper. ![]()
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