topic Re: Airfoil DAT to Spline in Fusion API and Scripts Forum

Airfoil DAT to Spline

Anonymous — Fri, 19 Sep 2025 05:28:46 GMT

Hi everyone!

I decided to create dedicated thread for my Airfoil DAT to Spline script.

Here you can share your ideas, ask questions and get support as from me as from other members of community who already using it.

On time of writing script has been downloaded over 800 times.

Most number of issues which I have got by e-mail with script was due to wrong DAT file structure.

For example, all values in one line, wrong delimiters, etc.

Proper DAT file should look like this

CLARK Y AIRFOIL
1.00000  0.00060
0.99000  0.00297
0.98000  0.00533
0.97000  0.00769
0.96000  0.01002
0.94000  0.01462
0.92000  0.01912
0.90000  0.02350
0.88000  0.02779
0.86000  0.03197
0.84000  0.03605
0.82000  0.04002
0.80000  0.04388
0.78000  0.04763
0.76000  0.05126
0.74000  0.05477
0.72000  0.05816
0.70000  0.06143
0.68000  0.06458
0.66000  0.06760
0.64000  0.07048
0.62000  0.07321
0.60000  0.07576
0.58000  0.07815
0.56000  0.08035
0.54000  0.08237
0.52000  0.08421
0.50000  0.08588
0.48000  0.08736
0.46000  0.08864
0.44000  0.08972
0.42000  0.09057
0.40000  0.09117
0.38000  0.09152
0.36000  0.09163
0.34000  0.09151
0.32000  0.09119
0.30000  0.09068
0.28000  0.09000
0.26000  0.08908
0.24000  0.08783
0.22000  0.08614
0.20000  0.08392
0.18000  0.08107
0.16000  0.07757
0.14000  0.07344
0.12000  0.06862
0.10000  0.06300
0.08000  0.05643
0.06000  0.04876
0.05000  0.04428
0.04000  0.03913
0.03000  0.03302
0.02000  0.02537
0.01200  0.01786
0.00800  0.01374
0.00400  0.00892
0.00200  0.00580
0.00100  0.00373
0.00050  0.00234
0.00000  0.00000
0.00050 -0.00467
0.00100 -0.00594
0.00200 -0.00781
0.00400 -0.01051
0.00800 -0.01429
0.01200 -0.01697
0.02000 -0.02027
0.03000 -0.02261
0.04000 -0.02452
0.05000 -0.02605
0.06000 -0.02713
0.08000 -0.02846
0.10000 -0.02938
0.12000 -0.02996
0.14000 -0.03024
0.16000 -0.03025
0.18000 -0.03005
0.20000 -0.02967
0.22000 -0.02914
0.24000 -0.02852
0.26000 -0.02782
0.28000 -0.02707
0.30000 -0.02631
0.32000 -0.02556
0.34000 -0.02482
0.36000 -0.02409
0.38000 -0.02336
0.40000 -0.02263
0.42000 -0.02190
0.44000 -0.02117
0.46000 -0.02044
0.48000 -0.01970
0.50000 -0.01896
0.52000 -0.01823
0.54000 -0.01749
0.56000 -0.01676
0.58000 -0.01602
0.60000 -0.01529
0.62000 -0.01456
0.64000 -0.01382
0.66000 -0.01309
0.68000 -0.01235
0.70000 -0.01162
0.72000 -0.01088
0.74000 -0.01015
0.76000 -0.00941
0.78000 -0.00868
0.80000 -0.00794
0.82000 -0.00721
0.84000 -0.00648
0.86000 -0.00574
0.88000 -0.00501
0.90000 -0.00427
0.92000 -0.00354
0.94000 -0.00280
0.96000 -0.00207
0.97000 -0.00170
0.98000 -0.00133
0.99000 -0.00097
1.00000 -0.00060

or like this

EPPLER 557 (w commas)
1.00000, 0.00000
0.99668, 0.00144
0.98772, 0.00542
0.97412, 0.01075
0.95547, 0.01657
0.93163, 0.02306
0.90304, 0.03026
0.87014, 0.03806
0.83341, 0.04631
0.79337, 0.05484
0.75055, 0.06343
0.70549, 0.07184
0.65873, 0.07984
0.61076, 0.08718
0.56211, 0.09364
0.51325, 0.09899
0.46460, 0.10306
0.41664, 0.10570
0.36975, 0.10679
0.32431, 0.10625
0.28069, 0.10407
0.23921, 0.10022
0.20011, 0.09480
0.16368, 0.08799
0.13028, 0.07998
0.10021, 0.07093
0.07373, 0.06101
0.05106, 0.05044
0.03238, 0.03945
0.01782, 0.02833
0.00748, 0.01743
0.00151, 0.00726
0.00045, 0.00385
0.00013, 0.00207
0.00001, 0.00038
0.00003, -0.00042
0.00011, -0.00119
0.00027, -0.00192
0.00052, -0.00263
0.00087, -0.00334
0.00129, -0.00406
0.00233, -0.00553
0.00361, -0.00701
0.00596, -0.00926
0.01636, -0.01627
0.03236, -0.02355
0.05314, -0.03040
0.07846, -0.03669
0.10798, -0.04235
0.14125, -0.04729
0.17779, -0.05132
0.21709, -0.05422
0.25862, -0.05560
0.30216, -0.05491
0.34786, -0.05189
0.39581, -0.04661
0.44615, -0.03942
0.49872, -0.03111
0.55291, -0.02243
0.60797, -0.01395
0.66303, -0.00619
0.71717, 0.00039
0.76936, 0.00548
0.81857, 0.00886
0.86373, 0.01046
0.90383, 0.01039
0.93794, 0.00884
0.96512, 0.00621
0.98462, 0.00324
0.99619, 0.00090
1.00000, 0.00000

The first line should be name of airfoil and new sketch will be renamed with use of it.

All following lines are X and Y coordinates (relatively to selected construction plane).

If the first and last coordinates are the same spline will be closed. If different, spline will be open.

As bonus I attached the latest (unpublished) version of "Airfoil DAT to Spline" script. Hopefully you know what to do with it.

Update: Attachment deleted.

Re: Airfoil DAT to Spline

Anonymous — Mon, 19 Mar 2018 10:27:44 GMT

Using the .zip archiv for installation on a macbook work well for me. Unpacking the .zip in the download folder and using the green "+" next to my scripts did the trick. The location of the script in the filesystem seems not to matter. Using the appstore download installation was reported successful, but no script was visible afterwards.

Re: Airfoil DAT to Spline

Anonymous — Mon, 19 Mar 2018 11:05:38 GMT

Klaus,

You right. Script location doesn't matter for Fusion 360.

I suppose default folders are useful when you going to backup all of them in one archive and restore them let's say on new computer.

In your case need to view details of the particular script to find where it is stored.

Re: Airfoil DAT to Spline

Anonymous — Wed, 06 Mar 2019 04:46:28 GMT

Hi everyone!

Just to let you know that in addendum to this script I published a new one.

Airfoil DAT Optimizer

Re: Airfoil DAT to Spline

Anonymous — Tue, 02 Apr 2019 07:31:04 GMT

Version 1.8 has been submitted to Autodesk. Stay tuned.

Re: Airfoil DAT to Spline

Anonymous — Sun, 05 May 2019 18:04:46 GMT

I have just downloaded Fusion 360 to my laptop, and tried to install the script, but no success.... 😞

I get a .pkg file, but it seems not to install automatically.

Sorry for the newbie question, but I really need it to work....

Could you help me?

Re: Airfoil DAT to Spline

Anonymous — Mon, 06 May 2019 04:55:48 GMT

Unfortunately I cannot help with MacOS.

The package has been successfully tested by other user.

Maybe someone can help you.

Re: Airfoil DAT to Spline

louis_dionne — Sun, 29 Sep 2019 23:44:28 GMT

I used the zip file or version 1.7 located in the first message in this topic. Unzipped in the folders where the other Python scripts are and added to My Scripts using the green +.

Re: Airfoil DAT to Spline

Anonymous — Mon, 04 Nov 2019 00:15:00 GMT

Thank you for the awesome plugins! They will be very useful for me in designing radio control gliders.

I was wondering if you could do a version of the DAT optimizer for the Mac? I would be happy to help with testing.

Regards,

Bill

Re: Airfoil DAT to Spline

mringNQ9L7 — Thu, 21 Nov 2019 18:10:27 GMT

I am using Windows but by default it downloaded the .pkg-version. If you are on windows, make sure to select "Windows" and it downloads an .msi-file which works like a charm!

Re: Airfoil DAT to Spline

Anonymous — Sun, 01 Mar 2020 11:36:53 GMT

Hello,
I cannot import a dat file in my Mac with Airfoil DAT to spline, each time I try I get the same answer. I have browsed the web and could not find what I do wrong. Thanks for your help.

Re: Airfoil DAT to Spline

Anonymous — Sun, 01 Mar 2020 16:32:19 GMT

Hi!

Could you post here first 10 lines of DAT file?

Re: Airfoil DAT to Spline

Anonymous — Sun, 01 Mar 2020 16:40:17 GMT

You need plain text editor if you going to edit DAT files.

Rich text format with fonts, etc. not supported.

Re: Airfoil DAT to Spline

Anonymous — Sat, 21 Mar 2020 12:26:28 GMT

For instance I copy paste that in text edit under a rtf format:

1.00000 0.0
0.99572 0.00057
0.98296 0.00218
0.96194 0.00463
0.93301 0.00770
0.89668 0.01127
0.85355 0.01522
0.80438 0.01945
0.75000 0.02384
0.69134 0.02823
0.62941 0.03247
0.56526 0.03638
0.50000 0.03978
0.43474 0.04248
0.37059 0.04431
0.33928 0.04484
0.30866 0.04509
0.27886 0.04504
0.25000 0.04466
0.22221 0.04397
0.19562 0.04295
0.17033 0.04161
0.14645 0.03994
0.12408 0.03795
0.10332 0.03564
0.08427 0.03305
0.06699 0.03023
0.05156 0.02720
0.03806 0.02395
0.02653 0.02039
0.01704 0.01646
0.00961 0.01214
0.00428 0.00767
0.00107 0.00349
0.0 0.0
0.00107 -0.00349
0.00428 -0.00767
0.00961 -0.01214
0.01704 -0.01646
0.02653 -0.02039
0.03806 -0.02395
0.05156 -0.02720
0.06699 -0.03023
0.08427 -0.03305
0.10332 -0.03564
0.12408 -0.03795
0.14645 -0.03994
0.17033 -0.04161
0.19562 -0.04295
0.22221 -0.04397
0.25000 -0.04466
0.27886 -0.04504
0.30866 -0.04509
0.33928 -0.04484
0.37059 -0.04431
0.43474 -0.04248
0.50000 -0.03978
0.56526 -0.03638
0.62941 -0.03247
0.69134 -0.02823
0.75000 -0.02384
0.80438 -0.01945
0.85355 -0.01522
0.89668 -0.01127
0.93301 -0.00770
0.96194 -0.00463
0.98296 -0.00218
0.99572 -0.00057
1.00000 0.0

Re: Airfoil DAT to Spline

Anonymous — Sat, 21 Mar 2020 12:41:00 GMT

I changed it in dat in the finder and it works now ! No idea why I was stuck !!

Re: Airfoil DAT to Spline

Anonymous — Sat, 21 Mar 2020 14:00:47 GMT

If you will see again error message, last two lines, you will understand the reason.

Script is reading file line by line.

First line converted to title of sketch.

Second and all following lines converted from text to float values.

If it cannot convert to number it fails. In you case it found following.

{\\fonttbl\\f0\\fmodern\\fcharset0

There are no coordinates. It's part of rich text format file, description of used font. This is why it failed.

If you found airfoil in http://airfoiltools.com/search/index then you don't need to copy-paste content.

Just export it in Selig format dat file. Link on right side.

This is example for CLARKY airfoil.

http://airfoiltools.com/airfoil/seligdatfile?airfoil=clarky-il

Re: Airfoil DAT to Spline&body

Anonymous — Sat, 21 Mar 2020 14:29:38 GMT

Yes, it’s fine.
Just make sure you selected «All files» in filter of file extensions when File Open dialog window will pop-up.
DAT file extension is just default value.

Re: Airfoil DAT to Spline&body

Anonymous — Sat, 21 Mar 2020 15:50:44 GMT

It drives me mad, it only works with my naca 0009 dat file and doesn't work with Naca 2424, no idea why, they both look alike.

I have to admit I do not undesrtand what you mean by:

"If you found airfoil in http://airfoiltools.com/search/index then you don't need to copy-paste content.

Just export it in Selig format dat file. Link on right side.

This is example for CLARKY airfoil.

http://airfoiltools.com/airfoil/seligdatfile?airfoil=clarky-il"

neither can I understand:
Just make sure you selected «All files» in filter of file extensions when File Open dialog window will pop-up.
DAT file extension is just default value.

I need more details to understand what you mean. I am not good with all that stuff...

Re: Airfoil DAT to Spline&body

Anonymous — Sat, 21 Mar 2020 16:21:07 GMT

I partly found what the problem is. The Naca 000P profile modified in dat shows no formating menu at the top of the window while the other profile modified in dat as well but is still in a text format. But no idea why ?

What did I do differently for the first file ?

Re: Airfoil DAT to Spline

Anonymous — Sat, 02 May 2020 23:26:33 GMT

i have got this error message after importing the dat file that i have downloaded from airfoil tools

---------------------------
Fusion 360
---------------------------
Failed:
Traceback (most recent call last):
File "C:/Users/sayf/AppData/Roaming/Autodesk/ApplicationPlugins/Airfoil_DAT_to_Spline_v1.8.bundle/Contents/Airfoil_DAT_to_Spline_v1.8.py", line 47, in notify
airfoil.Execute(sel0.entity, input1.value, input2.value, input3.value, input4.value, input5.value);
File "C:/Users/sayf/AppData/Roaming/Autodesk/ApplicationPlugins/Airfoil_DAT_to_Spline_v1.8.bundle/Contents/Airfoil_DAT_to_Spline_v1.8.py", line 134, in Execute
sketch = root.sketches.add(Plane);
File "C:/Users/sayf/AppData/Local/Autodesk/webdeploy/production/8b802e7a3c3d3db523b64fd80db49d9f63efcaf3/Api/Python/packages\adsk\fusion.py", line 26230, in add
return _fusion.Sketches_add(self, *args)
RuntimeError: 3 : not a planar entity

---------------------------
OK
---------------------------