Airfoil DAT to Spline

[scorpio9999]

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.

[devnarudolph]

Hi. I am having trouble importing my airfoil coordinates in fusion360. Can you please tell me what is wrong with this script. I keep getting this error message: wrong file format. Cannot convert Y coordinate.

Or the other error i get is Unknown DAT Format

NACA 23012 12%
1.00003 0.00126
0.99730 0.00170
0.98914 0.00302
0.97563 0.00518
0.95693 0.00812
0.93324 0.01176
0.90482 0.01602
0.87197 0.02079
0.83506 0.02597
0.79449 0.03145
0.75070 0.03712
0.70417 0.04285
0.65541 0.04854
0.60496 0.05405
0.55335 0.05924
0.50117 0.06397
0.44897 0.06811
0.39733 0.07150
0.34681 0.07402
0.29796 0.07554
0.25131 0.07597
0.20738 0.07524
0.16604 0.07320
0.12732 0.06915
0.09230 0.06265
0.06203 0.05382
0.03730 0.04324
0.01865 0.03176
0.00628 0.02030
0.00015 0.00956
0.00000 0.00000
0.00533 -0.00792
0.01557 -0.01401
0.03029 -0.01870
0.04915 -0.02248
0.07195 -0.02586
0.09868 -0.02922
0.12954 -0.03282
0.16483 -0.03660
0.20483 -0.04016
0.24869 -0.04283
0.29531 -0.04446
0.34418 -0.04510
0.39476 -0.04482
0.44650 -0.04371
0.49883 -0.04188
0.55117 -0.03945
0.60296 -0.03655
0.65360 -0.03327
0.70257 -0.02975
0.74930 -0.02607
0.79330 -0.02235
0.83407 -0.01866
0.87118 -0.01512
0.90420 -0.01180
0.93279 -0.00880
0.95661 -0.00621
0.97543 -0.00410
0.98901 -0.00254
0.99722 -0.00158
0.99997 -0.00126

[giulianoj.zennaro]

Thank you very much for the script, it is really useful !

One question, is there a way to make it compatible with parametric modeling ? Currently, although a user parameter can be used for example to define the chord length, if the parameter value is changed, the geometry is unfortunately not updated. Is there a simple workaround ?

[scorpio9999]

To all,

Due to new policy of Autodesk I cannot download free version of Fusion anymore. I lost possibility to design 3D things and I lost all my models as Fusion files I cannot open anymore.

Support of my scripts is terminated.

I will not respond to requests.

Say "thank you" to Autodesk.

Good luck!

P.S. I moved to FreeCAD.