Smooth airfoil surfaces - #1924
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sbryngelson merged 4 commits intoSep 29, 2026
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Claude Code Review Head SHA: bdda83b Files changed:
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@sbryngelson This is ready for review. |
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sbryngelson
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Sep 28, 2026
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these intrinsics gp%levelset_norm = matmul(rotation, normals) ! convert the normal sometimes cause compiler slowdowns or issues (esp. amdflang). nothing to worry about now just keep in mind. i think we have helpers for small matmuls |
Codecov Report❌ Patch coverage is Additional details and impacted files@@ Coverage Diff @@
## master #1924 +/- ##
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+ Coverage 61.07% 61.31% +0.24%
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Files 86 86
Lines 22662 22612 -50
Branches 3342 3327 -15
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+ Hits 13841 13865 +24
+ Misses 6351 6281 -70
+ Partials 2470 2466 -4 ☔ View full report in Codecov by Harness. 🚀 New features to boost your workflow:
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Improvements made to the airfoil levelset calculation. We were getting errors getting smooth profiles because of the method we were using to estimate levelset values. In current master, we generate several points, compute distance to each point, and take the distance and vector that points to the closest point. This causes many problems when points are too close to the surface and when the correct intersection lies between points.
To improve this, I have refactored the the airfoil levelset code to treat airfoil surfaces as a 2D STL model, where we project onto lines that connect the surface points. We also more-densely sample points near the tips of the airfoil to better resolve the areas of higher curvature. This produces significantly improved convergence in surface pressure values.
The following shows comparison to a 2D airfoil case with 400 grid cells per chord length.

The case file to generate this has been added to the examples and is skipped to not add additional tests compared to the per-existing 2D airfoil case. Accordingly, the golden files for the 2D IBM airfoil test have been regenerated.