Question about VSPAero Panel Method

[Lucas Huirne]

Dear community,

I am trying to do a panel method analysis of my model (see attached) to calculate the lift and drag distributions. I do however get nonsensical results (see attached image).

My settings are as follows:

When I remove the fuselage or use VLM the results become normal. I attached the VSP3 file in the attachments.

Does anyone know the reason for this? Thanks in advance

[Lucas Huirne]

Changing fuselage cross section to ellipse also does not work btw.

Op zaterdag 7 juni 2025 om 23:22:21 UTC+2 schreef Lucas Huirne:

[Brandon Litherland]

I think part of the issue is having unrealistically thin, reflexed TE airfoils.  OpenVSP is having a hard time rendering the upper and lower surfaces as two different sheets so I imagine that the errors in the solver are coming from that.  If you look at the solution in Viewer, you'll see that region having very high Cp values which tend to indicate a problem.  The trailing edge at your wingtips also show a lot of variability that doesn't make sense.  I recommend recreating a reflexed airfoil with more aft thickness to see if this doesn't help you.

[Lucas Huirne]

Thank you brandon for you answer! Changing the airfoil did indeed solve the problem. thanks!

Op maandag 9 juni 2025 om 16:37:06 UTC+2 schreef Brandon Litherland: