Modeling variable-span, multi-material airfoil sections in VABS

Modeling & Simulation VABS
1

I am designing a wing with a NACA 4412 airfoil, and my focus is the cross-sectional design. I need to model two different materials within each cross section, and the cross-section desing varies along the span. I can create the cross-section meshes in Gmsh, but I am not sure how to complete the full workflow in VABS to obtain the cross-sectional properties that can be used in NATASHA.

Is there anyone who can guide me through this process or share any videos, examples, or documentation that could help me move forward?

Thank you!

2

This may help: Analysis of cross-sections of a blade linking to RCAS — iVABS 0.10 documentation. The key here is simply a data pipeline: Gmsh output → VABS input and VABS output → NATASHA input.

3

Thanks Prof. Su.

I read what you sent. Right now I have license issue. I will check the process when my problem got solved.

4

Hi again Professor Su,

My license issue is now resolved, so I reviewed your earlier response. I still have some difficulties. The instructions you shared are for iVABS, but I am working with VABS, and I am not sure how to run the examples mentioned there. The explanation is very concise, and since I am new to this area, I need a bit more guidance to address my issues.

I am trying to obtain the stiffness matrices in VABS for the example wing design I attached. As you can see, I am using a NACA 4412 airfoil with a tree-structure design inside.

My main question is:

How should I model this cross section in Gmsh and generate a mesh that VABS can properly use?

If I can solve this first step, it will help me move forward with the rest of the workflow.

Thank you very much for your guidance and support.

My Schematic design
My Schematic design1844×612 75.7 KB

5

@Hadi It should be very easy to use iVABS. iVABS can be downloaded free from github, no license is needed. I don’t know whether @su.tian.22 has anything more to add.