inviscid analysis
XFLR5 is an analysis tool for airfoils, wings and planes
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techwinder
Hi André,
there seems to be a bug with the inviscid calculation.
After unticking the "Viscous" option, it seems like the viscous result is calculated instead (no convergence for some operating points). Additonally XFLR5 does not display the polar and exporting the polar produces an empty file, while the operating points are still shown in the object explorer.
I've attached an example file.
Cheers,
Stefan
The inviscid polars are of little interest since Cd = Cdi = 0.
Instead of restoring the generation of inviscid polars, I am tempted to remove the checkbox altogether and to make the analysis viscous by default. The invsicd Cp curve will still be available in the Cp graphs, if it is of any interest.
André
That is probably a good option. I just realised it because it's the first time I'm properly using the inviscid method after a lot of years of XFoil and XFLR5 for a very special case because the viscous analysis doesn't always converge. That said it is well outside the usual used case for XFLR5 or XFoil.
I would keep the inviscid Cp curve but apart from that it's probably a good idea to remove the option instead.
Cheers
Stefan
Fixed with commit 1444
Fixed in v6.59