University project
 

Hi,

I'm a student aeronautical engineering from Belgium and for my final year project I need to make an analysis of some airfoils.

Can someone please help me set op a correct mesh? I can import the geometry and create the C-mesh, but I can't define all the physics in the solver.

A more important question. If you generate the forces (lift and drag), you get a report with some numbers. Which numbers do you need to use for you lift component and drag component?

It would be super helpful if someone could guide me through the whole process. We didn't learn how to work with Ansys so I'm figuring everything out as I go.

I hope someone can help me.

There is a tutorial in FLUENT for this, have you had a go at that?

OJ

Yes, I tried a couple op tutorials and I'm able to complete them. But I could use some more help from someone who has more skills. And the lift and drag aren't properly explained.

When I do a test of a NACA 7420 at an angle of attack of 0° I get a L/D of 87.5858

I tried to set up my mesh for a model of 2 separate airfoils. When I try to subtract my bodies from my C-mesh, I get following error.

Operation would result in non-manifold bodies.

Does someone know how to make a C-mesh around 2 airfoils without getting this error?

Hey search forum and you will decent C-type meshes created in ICEM (Ansys meshing forum). If not, please let us know