Airfoil DAT to Spline
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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.