catherine a
unread,Oct 9, 2025, 12:27:29 PM (yesterday) Oct 9Sign in to reply to author
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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