Estimate the volume fraction of cells in a fixed space

A sample case for predicting the aerodynamic performances of an airfoil. It contains a mesh generator for an airfoil which is written in .m4 macro (Please refer to airfoil/system/blockMeshDict.m4). To generate a mesh, you need a airfoil data with .dat file extension. It is recommended to locate the airfoil data file in constant/airfoilData. Once the airfoil data file is prepared, you can generate the mesh by running meshgen.

Suppose that we want to generate a mesh for a Clarky airfoil. The airfoil data is prepared at constant/airfoilData/clarky.dat. To generate a mesh with blockMesh utility, the airfoil should be divided into 3 sections: upper, front, lower sections. Breakpoints between those three sections should be given in the airfoil data file with a character 'b'. For example,

constant/airfoilData/clarky.dat

...
0.36 0.0916266
0.34 0.0915079
0.32 0.0911857 /* Upper section until this point /
0.3 0.0906804 b / Break point here /
0.28 0.0900016 / Front section from this point */
0.26 0.089084
0.24 0.0878308
...

Then the airfoil data will be separated and generate sectional data file, such as airfoil.upper.z0, airfoil.upper.z1, airfoil.endPoint.z0, etc. The z0 represents the vertices on z=0 plane while z1 corresponds to z=0.1 plane. These manipulate files will be included in the blockMeshDict.m4 macro file to generate a blockMeshDict. To manipulate the airfoil data, one should run constant/airfoilData/airfoilmanip.sh as following.