trailing edge errors

[leiradom]

When I use machline to compute supersonic configurations, unphysical pressure distributions appear at the wing trailing edge kink or the wing trailing edge of wing-body combinations. After investigation, issues arise in the dipole calculation. Has this problem now been resolved?

[corygoates]

That's an issue we never got around to tackling. With this kind of supersonic panel method, you have to stitch the wake to the fuselage. Otherwise you get what you're seeing. MachLine can't do that stitching though.

[leiradom]

Thank you for your reply. I still really want to modify this program to add that functionality. As a developer who is quite familiar with it, do you think it is possible to implement this feature in MachLine? For example, would it be sufficient to generate vortex sheets along the fuselage to obtain accurate calculations, or do we also need to separate the vortex sheets for the fuselage and the wings at the wing-body junction and perform more complex processing, as is done in Panair?