Mesh Failure involving Multi-Section Wings with Cambered Airfoils

[Ron]

Software: OpenVSP 3.46.0

Wing Configuration and Sub-surface structure layout:
* Two-section half-wing with three cambered airfoils
* Each Wing section has different leading edge sweep angles
* Sub-surface structure includes:
   * Two spars at consistent chord locations: LE Spar (25% chord) and TE Spar (75% chord) for each wing section
   * Six ribs total: three per wing section located at 20%, 50%, and 80% section span

Problem:
When using Wings with cambered airfoils, the mesh generation fails or produces errors with the following issues:
 1. Sub-surface structures (ribs and spars) do not properly intersect with the wing skin
 2. As a result, Mesh quads and triangles do not align with sub-surface/skin intersections
 3. These mesh errors carry over into the exported BDF file

Key Observation:
The same wing configuration meshes successfully when using uncambered (symmetric) airfoils. No PolySpars are used in either case.

Question:
How can this meshing issue with cambered airfoils be resolved?

Ronald Jones...

[Rob McDonald]

I can't give much in the way of suggestions without playing with your model. Please post it if you can.

The PolySpar is a lot better than the plain spar.  It fixes several problems (particularly at the root and planform breaks).  I suggest you use PolySpar -- even in cases where you're doing a simple spar.

Rob

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