Learning Forum

[YashAgiwal]

Hello,

I am currently working on a project to reduce the wake region behind an airfoil. I am using NACA0009 for the project. In the project I am comparing the lift, drag and the length of trailing edge stagnation point. I was able to produce a structured/ O grid mesh around NACA0009 airfoil and generate the results, however I am finding it difficult to generate a structured mesh around the NACA0009 involving a slot/tunnel that runs from the leading edge to the trailing edge of the airfoil.

I have attached the image of the mesh near leading edge of the NACA0009 airfoil involving slot. I am able to produce body fitted grid for a part of airfoil, while it would be better to create the body fitted grid for the entire airfoil.

I am not sure whether the blocking process I adopted for meshing the slotted airfoil is correct.

It would be great if you guys can provide me the steps on blocking and generating O grid around this geometry..

I have attached the google link that has all the required files (Image, Mesh file and Geometry file).

 

 

 

[Rob]

Staff are not permitted to open/download attachments. Please repost the image. 

Chances are getting an O-grid & the passage will be incredibly difficult: why do you need a mesh like that?

[YashAgiwal]

Hello,

I need the flow to go through the passage as well. Basically I am dividing the airfoil into upper and lower section. 

Please find attached the mesh image.

[Rob]

Looks like the cells are clustering at the edges of the blocks. Also I suspect you've not got enough mesh through the hole.  Try using inflation & pave in Workbench Meshing. ICEM CFD is great for when you need 3d hex mesh, but I think you're making this overly hard for yourself.