FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 100,000 Max Cl/Cd: 39.21 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s171-il-100000-n5.txt Download as CSV file: xf-fx66s171-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4735 0.06537 0.06047 -0.0783 0.9990 0.0247
-11.000 -0.4796 0.05741 0.05213 -0.0894 0.9196 0.0247
-10.750 -0.4770 0.05132 0.04557 -0.0984 0.8755 0.0248
-10.500 -0.4746 0.04762 0.04154 -0.1018 0.8412 0.0252
-10.250 -0.4780 0.04495 0.03852 -0.1021 0.8153 0.0254
-10.000 -0.4772 0.04268 0.03595 -0.1015 0.7960 0.0257
-9.750 -0.4721 0.04056 0.03353 -0.1008 0.7802 0.0261
-9.500 -0.4639 0.03853 0.03120 -0.1001 0.7669 0.0266
-9.250 -0.4526 0.03659 0.02894 -0.0994 0.7554 0.0273
-9.000 -0.4387 0.03476 0.02680 -0.0986 0.7445 0.0281
-8.750 -0.4226 0.03308 0.02481 -0.0978 0.7347 0.0295
-8.500 -0.4043 0.03159 0.02294 -0.0971 0.7263 0.0313
-8.250 -0.3853 0.03027 0.02161 -0.0967 0.7176 0.0330
-8.000 -0.3649 0.02914 0.02033 -0.0962 0.7106 0.0351
-7.750 -0.3440 0.02798 0.01900 -0.0955 0.7030 0.0371
-7.500 -0.3232 0.02695 0.01779 -0.0948 0.6966 0.0400
-7.250 -0.3037 0.02603 0.01687 -0.0942 0.6900 0.0433
-7.000 -0.2832 0.02519 0.01591 -0.0934 0.6836 0.0467
-6.750 -0.2634 0.02434 0.01497 -0.0926 0.6782 0.0515
-6.500 -0.2431 0.02362 0.01420 -0.0919 0.6718 0.0569
-6.250 -0.2230 0.02283 0.01331 -0.0911 0.6666 0.0637
-6.000 -0.2015 0.02215 0.01253 -0.0906 0.6620 0.0740
-5.750 -0.1808 0.02136 0.01177 -0.0901 0.6568 0.0886
-5.500 -0.1596 0.02052 0.01100 -0.0897 0.6523 0.1169
-5.250 -0.1393 0.01945 0.01018 -0.0895 0.6487 0.1812
-5.000 -0.1206 0.01844 0.00983 -0.0891 0.6441 0.3124
-4.750 -0.0967 0.01837 0.00998 -0.0885 0.6395 0.3877
-4.500 -0.0703 0.01853 0.01001 -0.0881 0.6355 0.4297
-4.250 -0.0436 0.01876 0.01007 -0.0877 0.6319 0.4589
-4.000 -0.0178 0.01903 0.01027 -0.0872 0.6273 0.4810
-3.750 0.0085 0.01927 0.01040 -0.0867 0.6235 0.5002
-3.500 0.0350 0.01948 0.01048 -0.0863 0.6203 0.5168
-3.250 0.0621 0.01963 0.01049 -0.0860 0.6175 0.5300
-3.000 0.0880 0.01971 0.01049 -0.0857 0.6134 0.5406
-2.750 0.1146 0.01974 0.01041 -0.0856 0.6095 0.5488
-2.500 0.1419 0.01973 0.01026 -0.0856 0.6062 0.5555
-2.250 0.1696 0.01972 0.01012 -0.0856 0.6034 0.5613
-2.000 0.1969 0.01973 0.00996 -0.0858 0.6003 0.5681
-1.750 0.2230 0.01977 0.01000 -0.0856 0.5965 0.5724
-1.500 0.2499 0.01980 0.00996 -0.0856 0.5931 0.5781
-1.250 0.2775 0.01983 0.00986 -0.0858 0.5903 0.5845
-1.000 0.3051 0.01987 0.00982 -0.0858 0.5880 0.5896
-0.750 0.3319 0.01996 0.00985 -0.0858 0.5850 0.5954
-0.500 0.3577 0.02007 0.00995 -0.0858 0.5814 0.6009
-0.250 0.3840 0.02017 0.01004 -0.0856 0.5782 0.6061
0.000 0.4113 0.02026 0.01006 -0.0858 0.5755 0.6127
0.250 0.4388 0.02034 0.01010 -0.0858 0.5733 0.6186
0.500 0.4665 0.02045 0.01015 -0.0859 0.5713 0.6257
0.750 0.4906 0.02070 0.01047 -0.0857 0.5677 0.6324
1.000 0.5158 0.02088 0.01070 -0.0855 0.5643 0.6387
1.250 0.5424 0.02104 0.01083 -0.0855 0.5614 0.6459
1.500 0.5691 0.02115 0.01095 -0.0854 0.5590 0.6520
1.750 0.5970 0.02127 0.01103 -0.0856 0.5570 0.6595
2.000 0.6206 0.02154 0.01139 -0.0852 0.5537 0.6662
2.250 0.6439 0.02182 0.01175 -0.0848 0.5497 0.6744
2.500 0.6694 0.02198 0.01196 -0.0845 0.5464 0.6825
2.750 0.6968 0.02209 0.01207 -0.0846 0.5437 0.6925
3.000 0.7250 0.02215 0.01213 -0.0847 0.5415 0.7019
3.250 0.7454 0.02259 0.01274 -0.0839 0.5374 0.7123
3.500 0.7680 0.02293 0.01320 -0.0834 0.5339 0.7240
3.750 0.7926 0.02317 0.01352 -0.0831 0.5311 0.7367
4.000 0.8187 0.02331 0.01375 -0.0829 0.5288 0.7516
4.250 0.8459 0.02337 0.01388 -0.0828 0.5267 0.7702
4.500 0.8624 0.02389 0.01463 -0.0814 0.5226 0.7940
4.750 0.8805 0.02424 0.01521 -0.0800 0.5187 0.8287
5.000 0.9082 0.02437 0.01556 -0.0802 0.5158 0.8979
5.250 0.9422 0.02457 0.01579 -0.0818 0.5134 1.0000
5.500 0.9720 0.02479 0.01597 -0.0824 0.5115 1.0000
5.750 0.9834 0.02585 0.01720 -0.0808 0.5065 1.0000
6.000 1.0025 0.02650 0.01792 -0.0801 0.5024 1.0000
6.250 1.0278 0.02684 0.01829 -0.0800 0.4995 1.0000
6.500 1.0565 0.02703 0.01851 -0.0803 0.4973 1.0000
6.750 1.0723 0.02785 0.01943 -0.0792 0.4934 1.0000
7.000 1.0791 0.02905 0.02078 -0.0770 0.4879 1.0000
7.250 1.1020 0.02945 0.02125 -0.0766 0.4847 1.0000
7.500 1.1313 0.02957 0.02142 -0.0769 0.4823 1.0000
7.750 1.1341 0.03094 0.02294 -0.0743 0.4771 1.0000
8.000 1.1342 0.03241 0.02454 -0.0715 0.4716 1.0000
8.250 1.1584 0.03271 0.02492 -0.0712 0.4689 1.0000
8.500 1.1916 0.03261 0.02489 -0.0718 0.4669 1.0000
9.000 1.0883 0.04188 0.03436 -0.0592 0.4461 1.0000
9.250 1.1910 0.03678 0.02941 -0.0634 0.4522 1.0000
9.750 1.0395 0.05414 0.04680 -0.0559 0.4172 1.0000
10.000 1.0915 0.05105 0.04386 -0.0555 0.4205 1.0000
10.250 1.1396 0.04859 0.04154 -0.0553 0.4220 1.0000
11.750 1.0954 0.06908 0.06255 -0.0524 0.3676 1.0000
12.750 1.1756 0.06756 0.06150 -0.0492 0.3341 1.0000
13.000 1.1761 0.06972 0.06374 -0.0489 0.3172 1.0000
13.250 1.1778 0.07195 0.06602 -0.0487 0.2991 1.0000
13.500 1.1867 0.07328 0.06735 -0.0484 0.2785 1.0000
13.750 1.1853 0.07630 0.07040 -0.0485 0.2572 1.0000
14.000 1.1967 0.07718 0.07107 -0.0479 0.2215 1.0000
14.250 1.1938 0.08012 0.07368 -0.0477 0.1833 1.0000
14.500 1.1813 0.08472 0.07802 -0.0482 0.1521 1.0000
14.750 1.1674 0.08981 0.08292 -0.0491 0.1250 1.0000
15.000 1.1543 0.09500 0.08795 -0.0501 0.1020 1.0000
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