FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-100 AIRFOIL (fx60100-il) Reynolds number: 50,000 Max Cl/Cd: 42.58 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100-il-50000-n5.txt Download as CSV file: xf-fx60100-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3783 0.11724 0.10988 -0.0343 1.0000 0.0574
-10.000 -0.3702 0.11354 0.10621 -0.0342 1.0000 0.0535
-9.750 -0.3807 0.10821 0.10099 -0.0388 1.0000 0.0475
-9.500 -0.3718 0.10512 0.09793 -0.0379 1.0000 0.0462
-9.250 -0.3686 0.10178 0.09464 -0.0383 1.0000 0.0451
-9.000 -0.3677 0.09835 0.09130 -0.0389 1.0000 0.0441
-8.750 -0.3684 0.09488 0.08791 -0.0396 1.0000 0.0431
-8.500 -0.3714 0.09128 0.08442 -0.0404 1.0000 0.0422
-8.250 -0.3763 0.08778 0.08104 -0.0410 1.0000 0.0413
-8.000 -0.3848 0.08416 0.07755 -0.0415 1.0000 0.0403
-7.750 -0.3978 0.08043 0.07399 -0.0418 1.0000 0.0394
-7.250 -0.4296 0.06728 0.06092 -0.0533 1.0000 0.0365
-6.750 -0.4331 0.05891 0.05234 -0.0577 1.0000 0.0360
-6.500 -0.4284 0.05448 0.04771 -0.0604 1.0000 0.0358
-6.250 -0.4180 0.04995 0.04285 -0.0634 1.0000 0.0356
-6.000 -0.4019 0.04562 0.03811 -0.0662 1.0000 0.0355
-5.750 -0.3812 0.04169 0.03368 -0.0686 1.0000 0.0355
-5.500 -0.3576 0.03827 0.02973 -0.0704 1.0000 0.0358
-5.250 -0.3325 0.03546 0.02638 -0.0716 1.0000 0.0364
-5.000 -0.3088 0.03302 0.02370 -0.0723 1.0000 0.0383
-4.750 -0.2852 0.03131 0.02180 -0.0725 1.0000 0.0412
-4.500 -0.2608 0.02973 0.01995 -0.0724 1.0000 0.0439
-4.250 -0.2365 0.02832 0.01823 -0.0718 1.0000 0.0462
-4.000 -0.2120 0.02705 0.01680 -0.0715 1.0000 0.0488
-3.750 -0.1863 0.02596 0.01562 -0.0718 1.0000 0.0545
-3.500 -0.1597 0.02491 0.01447 -0.0723 1.0000 0.0663
-3.250 -0.1187 0.02305 0.01284 -0.0762 0.9970 0.1130
-3.000 -0.0775 0.02177 0.01303 -0.0803 0.9924 0.4051
-2.750 -0.0435 0.02238 0.01357 -0.0812 0.9846 0.4812
-2.500 -0.0111 0.02272 0.01377 -0.0817 0.9763 0.5206
-2.250 0.0250 0.02294 0.01377 -0.0832 0.9688 0.5518
-2.000 0.0587 0.02302 0.01365 -0.0843 0.9599 0.5751
-1.750 0.0941 0.02308 0.01351 -0.0859 0.9516 0.5979
-1.500 0.1295 0.02311 0.01341 -0.0874 0.9434 0.6178
-1.250 0.1619 0.02313 0.01327 -0.0884 0.9343 0.6372
-1.000 0.2004 0.02314 0.01314 -0.0905 0.9270 0.6561
-0.750 0.2310 0.02312 0.01308 -0.0911 0.9167 0.6737
-0.500 0.2641 0.02311 0.01299 -0.0921 0.9070 0.6930
-0.250 0.3029 0.02305 0.01288 -0.0941 0.8990 0.7137
0.000 0.3325 0.02300 0.01284 -0.0944 0.8878 0.7325
0.250 0.3642 0.02294 0.01279 -0.0950 0.8776 0.7539
0.500 0.4009 0.02275 0.01265 -0.0963 0.8698 0.7784
0.750 0.4274 0.02262 0.01261 -0.0958 0.8577 0.8073
1.000 0.4538 0.02239 0.01251 -0.0951 0.8456 0.8476
1.250 0.4861 0.02207 0.01231 -0.0956 0.8330 1.0000
1.500 0.5250 0.02215 0.01230 -0.0979 0.8220 1.0000
1.750 0.5649 0.02216 0.01226 -0.1000 0.8122 1.0000
2.000 0.5978 0.02228 0.01233 -0.1010 0.7990 1.0000
2.250 0.6305 0.02234 0.01237 -0.1016 0.7853 1.0000
2.500 0.6625 0.02240 0.01242 -0.1021 0.7714 1.0000
2.750 0.6938 0.02246 0.01252 -0.1024 0.7572 1.0000
3.000 0.7246 0.02253 0.01262 -0.1025 0.7429 1.0000
3.250 0.7556 0.02253 0.01265 -0.1025 0.7277 1.0000
3.500 0.7866 0.02250 0.01270 -0.1024 0.7118 1.0000
3.750 0.8142 0.02262 0.01287 -0.1019 0.6934 1.0000
4.000 0.8424 0.02269 0.01300 -0.1013 0.6746 1.0000
4.250 0.8723 0.02263 0.01298 -0.1008 0.6548 1.0000
4.500 0.8983 0.02275 0.01318 -0.0998 0.6310 1.0000
4.750 0.9255 0.02282 0.01327 -0.0989 0.6067 1.0000
5.000 0.9519 0.02295 0.01340 -0.0978 0.5805 1.0000
5.250 0.9764 0.02319 0.01364 -0.0966 0.5516 1.0000
5.500 0.9999 0.02355 0.01403 -0.0953 0.5216 1.0000
5.750 1.0219 0.02400 0.01449 -0.0940 0.4895 1.0000
6.000 1.0434 0.02452 0.01502 -0.0926 0.4575 1.0000
6.250 1.0634 0.02512 0.01558 -0.0910 0.4226 1.0000
6.500 1.0810 0.02586 0.01629 -0.0893 0.3828 1.0000
6.750 1.0970 0.02676 0.01705 -0.0874 0.3412 1.0000
7.000 1.1123 0.02780 0.01798 -0.0857 0.3017 1.0000
7.250 1.1275 0.02900 0.01907 -0.0840 0.2673 1.0000
7.500 1.1419 0.03034 0.02029 -0.0824 0.2369 1.0000
7.750 1.1556 0.03181 0.02167 -0.0807 0.2091 1.0000
8.000 1.1692 0.03334 0.02319 -0.0792 0.1851 1.0000
8.250 1.1824 0.03496 0.02474 -0.0776 0.1666 1.0000
8.500 1.1963 0.03659 0.02636 -0.0762 0.1500 1.0000
8.750 1.2107 0.03824 0.02802 -0.0748 0.1373 1.0000
9.000 1.2264 0.03995 0.02981 -0.0735 0.1263 1.0000
9.250 1.2417 0.04168 0.03172 -0.0722 0.1161 1.0000
9.500 1.2565 0.04346 0.03360 -0.0709 0.1079 1.0000
9.750 1.2746 0.04535 0.03573 -0.0698 0.1016 1.0000
10.000 1.2958 0.04751 0.03804 -0.0692 0.0965 1.0000
10.250 1.3139 0.04988 0.04075 -0.0683 0.0917 1.0000
10.500 1.3298 0.05199 0.04292 -0.0673 0.0872 1.0000
10.750 1.3374 0.05463 0.04590 -0.0656 0.0831 1.0000
11.000 1.3404 0.05739 0.04907 -0.0637 0.0795 1.0000
11.250 1.3461 0.06030 0.05226 -0.0622 0.0769 1.0000
11.500 1.3539 0.06322 0.05534 -0.0610 0.0746 1.0000
11.750 1.3532 0.06688 0.05929 -0.0595 0.0730 1.0000
12.000 1.3380 0.07115 0.06400 -0.0579 0.0719 1.0000
12.250 1.3195 0.07588 0.06911 -0.0570 0.0710 1.0000
12.500 1.2982 0.08123 0.07478 -0.0572 0.0703 1.0000
12.750 1.2740 0.08742 0.08126 -0.0586 0.0700 1.0000
13.000 1.2464 0.09476 0.08885 -0.0615 0.0702 1.0000
13.250 1.2157 0.10349 0.09778 -0.0660 0.0709 1.0000
13.500 1.1833 0.11381 0.10822 -0.0723 0.0718 1.0000
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Polar data table (+)
Polar graphs
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