How do I plug airfoil coordinates in?

[I'm Rick James]

I have a couple different sets of airfoil coordinates that I would like to use but I can't get them to my CNC buddy anytime soon. How do I plug these into an airfoil generator and get a profile?

I have Autocad and some airfoil generating program.

Anyone?

TIA, RJ

[Sparky Paul]

AutoCAD should be able to get the profile information in, in the form of a script file, which contains the x and y ordinates in a tabular form.
ISTR there's the need for a comma between the two points, and a space for the next pair.
Many years ago I ginned up a program that would compute an NACA profile, and output the results in AutoCAD and GenericCADD format.
I don't know what the current versions of AutoCAD do, the last version I have is v12.

[space_case]

Send them to me or just post them here, and I will give you a jpeg.

[I'm Rick James]

Very cool of you to do. They're in French so I home nothing is lost in translation!!! :D


SAlAZ_Emplanture_8%_1.8%_______(c) AZ(2005)
1.000733 0.000138
0.993884 -0.000041
0.980444 -0.000012
0.965279 0.000447
0.949422 0.001202
0.933392 0.002159
0.917265 0.003269
0.901101 0.004502
0.884910 0.005841
0.868703 0.007273
0.852485 0.008791
0.836250 0.010386
0.820016 0.012051
0.803766 0.013782
0.787504 0.015572
0.771292 0.017425
0.755060 0.019352
0.738753 0.021277
0.722423 0.023217
0.706096 0.025157
0.689769 0.027083
0.673503 0.028977
0.657249 0.030811
0.640941 0.032611
0.624659 0.034373
0.608374 0.036086
0.592055 0.037766
0.575775 0.039404
0.559497 0.040985
0.543185 0.042526
0.526917 0.044016
0.510650 0.045439
0.494347 0.046811
0.478087 0.048126
0.461815 0.049369
0.445517 0.050558
0.429263 0.051678
0.412997 0.052724
0.396720 0.053705
0.380497 0.054604
0.364258 0.055412
0.348032 0.056138
0.331862 0.056754
0.315663 0.057261
0.299516 0.057661
0.283405 0.057921
0.267282 0.058052
0.251256 0.058034
0.235246 0.057837
0.219305 0.057469
0.203441 0.056885
0.187623 0.056087
0.171919 0.055047
0.156296 0.053744
0.140803 0.052165
0.125470 0.050275
0.110313 0.048049
0.095444 0.045458
0.080850 0.042440
0.066695 0.038992
0.053157 0.035047
0.040403 0.030584
0.028987 0.025744
0.019584 0.020818
0.012628 0.016273
0.007889 0.012434
0.004748 0.009305
0.002669 0.006674
0.001321 0.004395
0.000476 0.002397
0.000048 0.000699
0.000153 -0.000801
0.001060 -0.002075
0.002711 -0.003159
0.005014 -0.004326
0.008182 -0.005692
0.012771 -0.007256
0.019720 -0.009169
0.029798 -0.011439
0.042498 -0.013766
0.056579 -0.015843
0.071247 -0.017581
0.086300 -0.018957
0.101606 -0.020042
0.117126 -0.020835
0.132845 -0.021428
0.148687 -0.021818
0.164669 -0.022071
0.180734 -0.022192
0.196915 -0.022235
0.213121 -0.022204
0.229422 -0.022122
0.245728 -0.022011
0.262063 -0.021857
0.278443 -0.021692
0.294791 -0.021500
0.311188 -0.021284
0.327589 -0.021062
0.343964 -0.020816
0.360398 -0.020558
0.376819 -0.020299
0.393225 -0.020023
0.409676 -0.019741
0.426113 -0.019459
0.442538 -0.019167
0.458990 -0.018872
0.475434 -0.018583
0.491876 -0.018292
0.508339 -0.018002
0.524793 -0.017719
0.541245 -0.017436
0.557711 -0.017157
0.574167 -0.016883
0.590618 -0.016609
0.607074 -0.016337
0.623517 -0.016072
0.639971 -0.015805
0.656441 -0.015541
0.672882 -0.015284
0.689322 -0.015022
0.705749 -0.014756
0.722088 -0.014461
0.738339 -0.014098
0.754553 -0.013670
0.770750 -0.013278
0.787016 -0.012804
0.803321 -0.012259
0.819650 -0.011644
0.836020 -0.011010
0.852403 -0.010332
0.868804 -0.009621
0.885190 -0.008866
0.901553 -0.008069
0.917891 -0.007212
0.934160 -0.006290
0.950291 -0.005265
0.966114 -0.004103
0.980810 -0.002705
0.993947 -0.000951
1.000733 0.000138


and the other half


SAlAZ_ext_8.5%_1.5%_______(c) AZ(2005)
1.000733 0.000115
0.993884 0.000071
0.980444 0.000302
0.965279 0.000901
0.949422 0.001749
0.933392 0.002772
0.917265 0.003928
0.901101 0.005194
0.884910 0.006553
0.868703 0.007997
0.852485 0.009516
0.836250 0.011105
0.820016 0.012755
0.803766 0.014467
0.787504 0.016226
0.771292 0.018037
0.755060 0.019909
0.738753 0.021783
0.722423 0.023664
0.706096 0.025537
0.689769 0.027393
0.673503 0.029217
0.657249 0.030985
0.640941 0.032721
0.624659 0.034422
0.608374 0.036076
0.592055 0.037699
0.575775 0.039283
0.559497 0.040813
0.543185 0.042305
0.526917 0.043749
0.510650 0.045130
0.494347 0.046464
0.478087 0.047743
0.461815 0.048954
0.445517 0.050114
0.429263 0.051210
0.412997 0.052233
0.396720 0.053195
0.380497 0.054079
0.364258 0.054875
0.348032 0.055592
0.331862 0.056204
0.315663 0.056711
0.299516 0.057114
0.283405 0.057383
0.267282 0.057527
0.251256 0.057528
0.235246 0.057355
0.219305 0.057017
0.203441 0.056469
0.187623 0.055711
0.171919 0.054717
0.156296 0.053461
0.140803 0.051928
0.125470 0.050083
0.110313 0.047897
0.095444 0.045341
0.080850 0.042350
0.066695 0.038919
0.053157 0.034984
0.040403 0.030529
0.028987 0.025696
0.019584 0.020781
0.012628 0.016252
0.007889 0.012425
0.004748 0.009301
0.002669 0.006686
0.001321 0.004429
0.000476 0.002441
0.000048 0.000708
0.000153 -0.000910
0.001060 -0.002409
0.002711 -0.003766
0.005014 -0.005200
0.008182 -0.006851
0.012771 -0.008755
0.019720 -0.011086
0.029798 -0.013836
0.042498 -0.016645
0.056579 -0.019156
0.071247 -0.021268
0.086300 -0.022969
0.101606 -0.024337
0.117126 -0.025376
0.132845 -0.026182
0.148687 -0.026755
0.164669 -0.027163
0.180734 -0.027414
0.196915 -0.027561
0.213121 -0.027609
0.229422 -0.027584
0.245728 -0.027509
0.262063 -0.027373
0.278443 -0.027205
0.294791 -0.026998
0.311188 -0.026750
0.327589 -0.026485
0.343964 -0.026184
0.360398 -0.025858
0.376819 -0.025520
0.393225 -0.025157
0.409676 -0.024778
0.426113 -0.024392
0.442538 -0.023986
0.458990 -0.023570
0.475434 -0.023154
0.491876 -0.022727
0.508339 -0.022294
0.524793 -0.021861
0.541245 -0.021422
0.557711 -0.020979
0.574167 -0.020537
0.590618 -0.020089
0.607074 -0.019637
0.623517 -0.019188
0.639971 -0.018731
0.656441 -0.018273
0.672882 -0.017817
0.689322 -0.017349
0.705749 -0.016875
0.722088 -0.016373
0.738339 -0.015808
0.754553 -0.015183
0.770750 -0.014591
0.787016 -0.013929
0.803321 -0.013205
0.819650 -0.012423
0.836020 -0.011630
0.852403 -0.010803
0.868804 -0.009952
0.885190 -0.009071
0.901553 -0.008161
0.917891 -0.007207
0.934160 -0.006204
0.950291 -0.005124
0.966114 -0.003938
0.980810 -0.002563
0.993947 -0.000898
1.000733 0.000115


Thanks Space Case, I really appreciate it..

RJ

[space_case]

Not the best, but they may help. I thought I could plot them a bit smoother but I've been doing CNC for so long I forgot. I think if you print them, they will come out smooth... ??

I think this is the order in which you gave them...

http://i3.photobucket.com/albums/y53/aerospace_case/foil1.jpg


http://i3.photobucket.com/albums/y53/aerospace_case/foil2.jpg

[space_case]

I see some reflex. I guess this is for a flying wing?

[I'm Rick James]

I see some reflex. I guess this is for a flying wing?

Yessiree indeed.

Thank you very much for the quick work. I don't think NASA style prescision is needed for this project so I'll print it out and get it smoothed with my copier at work.

With a slight forward sweep and lightest wing loading possible, this one should be a stable glider.

RJ

[space_case]

Not a problem. I'm looking at a job in SoCal so just be sure to show me the hip flying spots if I come out there.

I think it prints out pretty smooth. I used to print them out, measure with a ruler, and then use the % function on a copier to scale the image to the desired chord.

[I'm Rick James]

Look me up if your out this way.

If you slope fly, I'll steer ya in the right direction.

If you fly RC Combat, you'll be in good hands too.

The rest of it, I'll watch as you show me the ropes!

[Batmanwpg]

You can also use Profili to add these co-ordinates to generate the airfoil then export the file as DFX into AutoCad

[HELModels]

Not sure if you can do any better than Cl of 0.6 with a flying wing, but here is a quick Xfoil plot at a Re of 129,000 - seems reasonable on a slope.