SG6050 (sg6050-il)
SG6050 - Selig / Giguere SG6050 wind turbine airfoil
| Details | Dat file | Parser | |
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(sg6050-il) SG6050 Selig / Giguere SG6050 wind turbine airfoil Max thickness 16% at 31.5% chord. Max camber 3.1% at 48.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SG6050
1.00000 .00500
.99776 .00537
.99140 .00676
.98154 .00926
.96862 .01259
.95269 .01647
.93376 .02088
.91202 .02588
.88771 .03145
.86107 .03753
.83238 .04406
.80189 .05095
.76990 .05810
.73669 .06537
.70255 .07260
.66777 .07960
.63248 .08606
.59676 .09188
.56085 .09699
.52482 .10124
.48875 .10465
.45288 .10717
.41735 .10875
.38234 .10944
.34802 .10919
.31453 .10799
.28208 .10588
.25080 .10283
.22077 .09891
.19219 .09414
.16515 .08856
.13976 .08230
.11615 .07543
.09444 .06803
.07476 .06021
.05720 .05205
.04182 .04366
.02873 .03517
.01798 .02669
.00963 .01842
.00379 .01050
.00049 .00319
.00048 -.00309
.00410 -.00909
.01067 -.01542
.01982 -.02164
.03139 -.02736
.04566 -.03227
.06289 -.03656
.08289 -.04048
.10541 -.04399
.13028 -.04708
.15727 -.04970
.18616 -.05179
.21672 -.05320
.24887 -.05376
.28257 -.05342
.31773 -.05203
.35454 -.04962
.39318 -.04660
.43322 -.04364
.47392 -.04093
.51485 -.03820
.55578 -.03543
.59645 -.03264
.63657 -.02986
.67587 -.02715
.71406 -.02454
.75081 -.02210
.78578 -.01978
.81865 -.01740
.84949 -.01489
.87833 -.01247
.90477 -.01041
.92847 -.00874
.94910 -.00744
.96643 -.00638
.98044 -.00548
.99101 -.00494
.99770 -.00489
1.00000 -.00500
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Polars for SG6050 (sg6050-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6050-il | 50,000 | 9 | 8.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 50,000 | 5 | 25.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 100,000 | 9 | 50 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 100,000 | 5 | 52.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 200,000 | 9 | 74.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 200,000 | 5 | 73.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 500,000 | 9 | 105.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 500,000 | 5 | 97.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6050-il | 1,000,000 | 9 | 126.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6050-il | 1,000,000 | 5 | 113 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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