Free Flight, Free Speech

@Bomber

Sweet.
That's encouraging.

I'm surprised to see that the smoothing by itself had such nice effect on the polars!

Had you tried out the spanwise projectors (like 2_2.csv, or 5_5.csv) to check if/how the shape transformation is making sense too?
In shape and in polars obtained.

Best,

does something come to mind about why in the resulting polars, for lift given drag, in the green plot, there is no lift coefficients calculated for drag coefficients about 0.175?

IAHM-COL wrote:@Bomber

Had you tried out the spanwise projectors (like 2_2.csv, or 5_5.csv) to check if/how the shape transformation is making sense too?
In shape and in polars obtained.

Best,

If you could redo but for 8 sections only... I'd have a like for like comparison.... but as yours is in split into 10, it makes it a bit different.

regards

Simon

IAHM-COL wrote:does something come to mind about why in the resulting polars, for lift given drag, in the green plot, there is no lift coefficients calculated for drag coefficients about 0.175?

I'm not sure I understand as I'm not seeing this in the graph

Ah I see what you're saying.... those are plots per AoA

bomber wrote:
If you could redo but for 8 sections only... I'd have a like for like comparison.... but as yours is in split into 10, it makes it a bit different.

regards

Simon

Yes. I can do.
Do you mean every 0.125 evenly?
like

[0,0.125,0.25, .... 1] ?

bomber wrote:

IAHM-COL wrote:does something come to mind about why in the resulting polars, for lift given drag, in the green plot, there is no lift coefficients calculated for drag coefficients about 0.175?

I'm not sure I understand as I'm not seeing this in the graph

Ah I see what you're saying.... those are plots per AoA

an image is worth 1000+ words
an image with words is worth 1000+words words

I think it's 1/7 for an 8 wing split

0 = root
0.1428571428571429‬
0.2857142857142857
0.4285714285714286‬
0.5714285714285714‬
0.7142857142857143‬
0.8571428571428571‬
1‬ = tip

https://github.com/IAHM-COL/py-JSBsim-g ... src/output

I think this is what we want
the wing is split in even 8 segments
0 = chord
7 = tip
1-6 = internal segments going from low (chord wise) to high (tip wise)

Used this segments proprortions:

bomber wrote:I think it's 1/7 for an 8 wing split

You are exactly right.
I didnt introduce the numbers myself, so even my brain fooled me, the software said, no no,.

It seems we are good now.

See post above
I did not update images or video, as it is not fully necessary for this test.
but csv files are up to date

and image of the wing within the Autocad file..

the white dims show the dimensions for the centre of each wing section

https://drive.google.com/file/d/11edKmP ... sp=sharing