Hello! would it be possible to have an explanation of generation this C-mesh? For instance at 3:20 to 3:40 why do you select those specific points on the airfoil to draw edges out to the far field? What is the method used to determine which points should be used to select those vertices?
There is no particular method for that. The chosen points don't really matter as long as the mesh cells are orthogonal near that location, so you should not select points too close to the leading edge of the airfoil (also not to far from the leading edge). Also I would recommend to take the two points which are symmetrical around horizontal axis, such that the mesh would have a better structure.
Hi, I'm having an issue with the transfinite tool. I don't suppose you know why this is. I created an additional area, which I termed the boundary layer. I build the airfoil and boundary layer with the bspline tool. The problem that I have is once, I use the transfinite tool, the elements near to the lines I have drawn that are normal to the object inside the flow become skewed. I'm not sure if this is an issue with using bspline or something else.
Hey, sorry for the late reply. It's difficult tell where the problem lies. Is it possible that you did not select the additional area while recombining the surfaces? Also if you use a uniform point distribution instead of bspline, do you get the same problem?
I'm using this to learn how to develop a mesh for my studies. thanks!
Hello! would it be possible to have an explanation of generation this C-mesh? For instance at 3:20 to 3:40 why do you select those specific points on the airfoil to draw edges out to the far field? What is the method used to determine which points should be used to select those vertices?
There is no particular method for that. The chosen points don't really matter as long as the mesh cells are orthogonal near that location, so you should not select points too close to the leading edge of the airfoil (also not to far from the leading edge). Also I would recommend to take the two points which are symmetrical around horizontal axis, such that the mesh would have a better structure.
This was extremely useful. Thank you very much!
It helped a lot. Thank you
Do you know how we can add period boundary condition to both sides ?
Well done! Thanks.
Hi, I'm having an issue with the transfinite tool. I don't suppose you know why this is. I created an additional area, which I termed the boundary layer. I build the airfoil and boundary layer with the bspline tool. The problem that I have is once, I use the transfinite tool, the elements near to the lines I have drawn that are normal to the object inside the flow become skewed. I'm not sure if this is an issue with using bspline or something else.
Hey, sorry for the late reply. It's difficult tell where the problem lies. Is it possible that you did not select the additional area while recombining the surfaces?
Also if you use a uniform point distribution instead of bspline, do you get the same problem?
How about to create a C-Mesh if the AoA is different than zero?
I guess same procedure but you need to download .dat file of your airfoil already in that AoA.
Amazing
and now, to openfoam? how do i do it?