FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 50,000 Max Cl/Cd: 42.65 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100sm-il-50000-n5.txt Download as CSV file: xf-fx60100sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX60-100 10.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3886 0.08921 0.08232 -0.0434 1.0000 0.0462
-8.250 -0.3900 0.08624 0.07945 -0.0429 1.0000 0.0457
-8.000 -0.3954 0.08321 0.07653 -0.0426 1.0000 0.0451
-7.750 -0.4036 0.08012 0.07357 -0.0423 1.0000 0.0446
-7.500 -0.4108 0.07634 0.06990 -0.0432 1.0000 0.0440
-7.250 -0.4176 0.07199 0.06563 -0.0454 1.0000 0.0434
-7.000 -0.4243 0.06681 0.06047 -0.0494 1.0000 0.0426
-6.750 -0.4287 0.06160 0.05519 -0.0535 1.0000 0.0419
-6.500 -0.4275 0.05629 0.04967 -0.0578 1.0000 0.0413
-6.250 -0.4187 0.05112 0.04418 -0.0618 1.0000 0.0408
-6.000 -0.4030 0.04634 0.03895 -0.0655 1.0000 0.0404
-5.750 -0.3824 0.04227 0.03439 -0.0683 1.0000 0.0406
-5.500 -0.3592 0.03898 0.03061 -0.0703 1.0000 0.0420
-5.250 -0.3340 0.03613 0.02723 -0.0719 1.0000 0.0439
-5.000 -0.3081 0.03374 0.02432 -0.0727 1.0000 0.0454
-4.750 -0.2827 0.03175 0.02190 -0.0729 1.0000 0.0463
-4.500 -0.2587 0.02991 0.01983 -0.0727 1.0000 0.0475
-4.250 -0.2355 0.02845 0.01828 -0.0723 1.0000 0.0495
-4.000 -0.2116 0.02735 0.01705 -0.0721 1.0000 0.0538
-3.750 -0.1870 0.02645 0.01589 -0.0718 1.0000 0.0589
-3.500 -0.1616 0.02534 0.01478 -0.0721 1.0000 0.0644
-3.250 -0.1239 0.02428 0.01359 -0.0748 0.9955 0.0770
-3.000 -0.0796 0.02253 0.01220 -0.0793 0.9912 0.1399
-2.750 -0.0409 0.02192 0.01285 -0.0824 0.9851 0.4313
-2.500 -0.0119 0.02272 0.01383 -0.0818 0.9762 0.5193
-2.250 0.0250 0.02289 0.01374 -0.0835 0.9690 0.5461
-2.000 0.0579 0.02294 0.01359 -0.0845 0.9600 0.5693
-1.750 0.0937 0.02300 0.01347 -0.0861 0.9521 0.5916
-1.500 0.1287 0.02303 0.01332 -0.0876 0.9434 0.6120
-1.250 0.1619 0.02304 0.01321 -0.0887 0.9342 0.6311
-1.000 0.2002 0.02304 0.01309 -0.0907 0.9265 0.6516
-0.750 0.2311 0.02304 0.01301 -0.0914 0.9161 0.6703
-0.500 0.2649 0.02301 0.01294 -0.0925 0.9069 0.6898
-0.250 0.3015 0.02297 0.01285 -0.0942 0.8982 0.7117
0.000 0.3308 0.02292 0.01281 -0.0944 0.8873 0.7329
0.250 0.3636 0.02283 0.01275 -0.0951 0.8776 0.7574
0.500 0.3978 0.02264 0.01262 -0.0959 0.8687 0.7857
0.750 0.4235 0.02248 0.01256 -0.0952 0.8568 0.8191
1.000 0.4504 0.02221 0.01243 -0.0946 0.8453 0.8744
1.250 0.4879 0.02206 0.01228 -0.0965 0.8336 1.0000
1.500 0.5298 0.02206 0.01218 -0.0991 0.8244 1.0000
1.750 0.5631 0.02219 0.01225 -0.1002 0.8115 1.0000
2.000 0.5959 0.02230 0.01232 -0.1010 0.7985 1.0000
2.250 0.6283 0.02239 0.01240 -0.1017 0.7854 1.0000
2.500 0.6603 0.02246 0.01246 -0.1021 0.7719 1.0000
2.750 0.6920 0.02250 0.01252 -0.1024 0.7579 1.0000
3.000 0.7231 0.02254 0.01261 -0.1025 0.7434 1.0000
3.250 0.7538 0.02256 0.01267 -0.1025 0.7281 1.0000
3.500 0.7843 0.02258 0.01272 -0.1023 0.7121 1.0000
3.750 0.8147 0.02257 0.01275 -0.1021 0.6955 1.0000
4.000 0.8435 0.02263 0.01290 -0.1016 0.6771 1.0000
4.250 0.8705 0.02274 0.01308 -0.1008 0.6564 1.0000
4.500 0.9000 0.02272 0.01307 -0.1002 0.6358 1.0000
4.750 0.9250 0.02290 0.01330 -0.0991 0.6106 1.0000
5.000 0.9504 0.02305 0.01351 -0.0979 0.5837 1.0000
5.250 0.9748 0.02325 0.01371 -0.0967 0.5540 1.0000
5.500 0.9982 0.02354 0.01396 -0.0953 0.5223 1.0000
5.750 1.0205 0.02393 0.01433 -0.0938 0.4892 1.0000
6.000 1.0409 0.02446 0.01484 -0.0923 0.4537 1.0000
6.250 1.0606 0.02507 0.01537 -0.0907 0.4175 1.0000
6.500 1.0786 0.02583 0.01608 -0.0890 0.3790 1.0000
6.750 1.0954 0.02673 0.01687 -0.0873 0.3397 1.0000
7.000 1.1109 0.02780 0.01782 -0.0856 0.3017 1.0000
7.250 1.1260 0.02901 0.01892 -0.0839 0.2660 1.0000
7.500 1.1408 0.03035 0.02015 -0.0823 0.2363 1.0000
7.750 1.1555 0.03178 0.02148 -0.0808 0.2116 1.0000
8.000 1.1708 0.03324 0.02290 -0.0794 0.1913 1.0000
8.250 1.1877 0.03474 0.02443 -0.0781 0.1760 1.0000
8.500 1.2047 0.03625 0.02597 -0.0769 0.1622 1.0000
8.750 1.2219 0.03779 0.02760 -0.0758 0.1498 1.0000
9.000 1.2413 0.03943 0.02935 -0.0748 0.1401 1.0000
9.250 1.2598 0.04110 0.03103 -0.0738 0.1312 1.0000
9.500 1.2761 0.04283 0.03299 -0.0727 0.1219 1.0000
9.750 1.2949 0.04480 0.03519 -0.0717 0.1144 1.0000
10.000 1.3102 0.04669 0.03721 -0.0706 0.1070 1.0000
10.250 1.3218 0.04892 0.03974 -0.0691 0.0998 1.0000
10.500 1.3338 0.05098 0.04191 -0.0677 0.0936 1.0000
10.750 1.3386 0.05354 0.04480 -0.0658 0.0879 1.0000
11.000 1.3412 0.05585 0.04733 -0.0638 0.0824 1.0000
11.250 1.3459 0.05846 0.05005 -0.0622 0.0777 1.0000
11.500 1.3380 0.06179 0.05384 -0.0601 0.0738 1.0000
11.750 1.3341 0.06471 0.05695 -0.0587 0.0700 1.0000
12.000 1.3362 0.06754 0.05978 -0.0577 0.0664 1.0000
12.250 1.3189 0.07227 0.06498 -0.0569 0.0647 1.0000
12.500 1.3007 0.07745 0.07053 -0.0570 0.0631 1.0000
12.750 1.2810 0.08319 0.07659 -0.0581 0.0620 1.0000
13.000 1.2587 0.08979 0.08347 -0.0603 0.0614 1.0000
13.250 1.2319 0.09781 0.09175 -0.0640 0.0616 1.0000
13.500 1.2000 0.10780 0.10195 -0.0696 0.0629 1.0000
13.750 1.1674 0.11923 0.11353 -0.0768 0.0643 1.0000
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Polar data table (+)
Polar graphs
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