|March 20, 2013, 22:58||
mesh size requirement for NACA0015 airfoil
Join Date: May 2011
Posts: 9Rep Power: 7
I am simulating a 2D compressible viscous laminar flow around NACA0015 airfoil (without turbulence model). The chord length of airfoil is 0.2m. The triangular mesh is used. To resolve the boundary layer near the airfoil surface, what is the grid resolution required near the airfoil surface, (i.e. the edge length of triangular element near the solid wall)? How many layers of fine grid are needed near the wall? (My simulation must be time accurate.)
I have generated a mesh with edge length of 0.1mm along the airfoil. But the solution is not converged.
Can you give me some advice?
By the way, is there any free triangular mesh for NACA airfoil on internet?
|Thread||Thread Starter||Forum||Replies||Last Post|
|Star CCM Overset Mesh Error (Rotating Turbine)||thezack||CD-adapco||7||October 12, 2016 11:14|
|Number of cells in mesh don't match with size of cellLevel||colinB||OpenFOAM Native Meshers: snappyHexMesh and Others||11||January 13, 2015 12:47|
|[ANSYS Meshing] max mesh element size||ulalala||ANSYS Meshing & Geometry||8||January 20, 2013 18:30|
|2D hex mesh on multi element airfoil||Verfblikje||Open Source Meshers: Gmsh, Netgen, CGNS, ...||0||January 19, 2012 11:55|
|How to decide the mesh size?||echo||CD-adapco||1||May 23, 2006 05:34|