A320neo model — spikes in load distribution and unusually low drag polar (VSPAERO 3.45.4, Windows)

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catherine a

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Oct 9, 2025, 12:27:29 PM (yesterday) Oct 9
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Hello,

I’m modelling an Airbus A320neo in OpenVSP and running analyses in VSPAERO to try obtain a drag polar, however, my results appear unusually low, and the load distribution shows sharp spikes near the wing–fuselage intersection.

I’ve tried refining the geometry, adjusting wing sections to align better with the fuselage and re-meshing the intersection region, but the spikes remain.  I’m not sure whether they could be influencing the drag results, but I’d like to make sure the setup is correct.

Has anyone encountered similar behaviour, or could suggest additional checks or validation steps I might try?

I have attached load distribution and drag polar graphs for reference, as well as the wing-fuselage intersection.
(If it would help to attach the .vsp3 model, I’m happy to do so.)

I’m using OpenVSP v3.45.4 on Windows.

Many thanks in advance for any guidance,
Catherine
current drag polar plot.PNG
top down view of 'MeshGeom_NGon'.PNG
current load distribution plot.PNG
tangential view of 'MeshGeom_NGon'.PNG
VSPAERO window.PNG

Rob McDonald

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Oct 9, 2025, 12:34:40 PM (yesterday) Oct 9
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3.46.0 includes a bug fix related to how the trailing edge wake behaves where it intersects other bodies.  It might help with the lift distribution spikes in this case.

Otherwise, please do post your *.vsp3 file so people can try more to help.

Rob


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catherine a

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4:49 AM (11 hours ago) 4:49 AM
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Hello,

Thank you for your quick response, I've downloaded version 3.46.0 and ran the analysis again, but unfortunately the spikes are still showing.

I have attached my model in case anyone has a chance to look at it.

Thanks
Catherine
a320neo.vsp3
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