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As I already mentioned somewhere else, I am currently working on an airfoil workbench. I will posts updates in this topic. The work has 3 targets:
1. calibrating/modifying spline-foils to foils given by coordinates
2. optimizing spline foils (reducing drag with libxfoil)
3. interpolation of drag-computation with neural networks (not yet sure if this is a good idea)


1.
The current functionality is mainly the calibration and interactive modification of spline foils (I called them parafoil's -> parametric foils). This tool helps to create good approximations of airfoil coordinates by using a calibration method (least-square method from scipy). I decided to fix the number of poles of a parafoil. This makes the calibration task easier and also will help later on with the wing creation.



added nose-tangent and table to modify pole-coordinates and weights:

I'd like to include this as a new WB in the 0.19 release notes. Can you post a good description and maybe a nice screenshot either here or in the release notes thread?

The release notes thread was rather hard to find. Should it be pinned or moved to Announcments or both?

chrisb wrote: ↑Thu Dec 12, 2019 9:42 am Should it be pinned or moved to Announcments or both?

Is this thumb up for pin or move or both ?

chrisb wrote: ↑Thu Dec 12, 2019 11:13 am Is this thumb up for pin or move or both ?

lol, my vote is to pin it

Joel_graff wrote: ↑Thu Dec 12, 2019 3:11 am I'd like to include this as a new WB in the 0.19 release notes. Can you post a good description and maybe a nice screenshot either here or in the release notes thread?

I would like to make some progress first, as currently, not much functionality is provided.

Kunda1 wrote: ↑Thu Dec 12, 2019 3:05 pm lol, my vote is to pin it

I pinned it, we can easily return to the current state by unpinning.

I need a solution for finding the leading-edge of an foil given by coordinates. Currently I am using the point with the smallest x-value as the leading-edge. But this is not coorect. I guess a better definition of the leading edge is the intersection of the camber-curve and the airfoil. But I am not sure how to compute this point. Maybe someone has an idea.

What is the definition of the leading edge? I think, I have a feeling,but it is better to have a well defined concept.