fin smith asked 1 week ago
i’m i’m designing a blended wing aircraft for my university dissertation and i’d really like to use the optimisation program,
when i look at the Cp distribution the trailing edge has a more negative Cp value which i assume is wrong,
i simplified the design but still the same thing, im wondering if ive done something wrong or if the solver just has a problem with solving this kind of geometry, i thought it may be the wrong was round but redesigned it and had the same issue.
any info on how i can edit the design or fix the issue would be greatly appreciated
Difficult to say what or if there is an issue without more information.
Blended wings should pose no particular problem.
The quality of the mesh and the analysis settings should be the first things to investigate.
André
https://www.dropbox.com/scl/fi/06iy4gl9ip4khz7hgd8y9/Cp.png?rlkey=nkcv13wi78jhkqypuh06cn9t3&st=qvrdhlhf&dl=0
here’s the Cp distribution, its less noticeable now but I think its struggling with the long chord section which may be due higher Reynolds number, ive played around with the panels but still always get a lower pressure at the leading edge, this might be true but it just makes me uneasy when finding bending moments, I appreciate the quick response and I can link you the project if you wish
best wishes
fin smith
Looks good as far as I can tell.
The inviscid panel solver ignores Reynolds numbers which are only used to evaluate the viscous drag.
Keep in mind that the leading and trailing edges are areas of high pressure gradients, which a usual wing mesh is not able to resolve properly.
You can visualize the Cp profiles in the Cp view (F9).