E64 (8.45%) (e64-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 100,000 Max Cl/Cd: 63.97 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e64-il-100000.txt Download as CSV file: xf-e64-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3847 0.10484 0.09987 -0.0325 1.0000 0.0843
-8.500 -0.3995 0.10364 0.09880 -0.0345 1.0000 0.0857
-8.250 -0.4200 0.10271 0.09802 -0.0354 1.0000 0.0862
-8.000 -0.4001 0.09675 0.09204 -0.0328 1.0000 0.0883
-7.750 -0.3910 0.09378 0.08908 -0.0306 1.0000 0.0910
-7.500 -0.3947 0.09155 0.08692 -0.0293 1.0000 0.0938
-7.250 -0.4059 0.08974 0.08522 -0.0278 1.0000 0.0961
-7.000 -0.4229 0.08799 0.08359 -0.0282 1.0000 0.0985
-6.750 -0.4436 0.08496 0.08059 -0.0399 1.0000 0.1003
-6.500 -0.4367 0.08126 0.07700 -0.0321 1.0000 0.1019
-6.250 -0.4313 0.07899 0.07478 -0.0276 1.0000 0.1048
-6.000 -0.4305 0.07624 0.07206 -0.0279 1.0000 0.1089
-5.750 -0.4301 0.07080 0.06652 -0.0392 1.0000 0.1154
-5.500 -0.4255 0.06889 0.06472 -0.0329 1.0000 0.1184
-5.250 -0.4144 0.06414 0.05981 -0.0407 1.0000 0.1298
-5.000 -0.4092 0.06241 0.05818 -0.0354 1.0000 0.1341
-4.750 -0.3955 0.05850 0.05418 -0.0390 1.0000 0.1462
-4.500 -0.3789 0.05498 0.05054 -0.0419 1.0000 0.1596
-4.250 -0.3610 0.05175 0.04719 -0.0439 1.0000 0.1737
-4.000 -0.3424 0.04876 0.04412 -0.0451 1.0000 0.1883
-3.750 -0.2425 0.03040 0.02286 -0.0623 1.0000 0.0591
-3.500 -0.2127 0.02723 0.01933 -0.0634 1.0000 0.0572
-3.250 -0.1834 0.02503 0.01670 -0.0637 1.0000 0.0563
-3.000 -0.1558 0.02341 0.01474 -0.0637 1.0000 0.0565
-2.750 -0.1296 0.02243 0.01343 -0.0632 1.0000 0.0597
-2.500 -0.1037 0.02108 0.01215 -0.0633 1.0000 0.0668
-2.250 -0.0773 0.02012 0.01112 -0.0631 1.0000 0.0742
-2.000 -0.0490 0.01905 0.01023 -0.0634 1.0000 0.1035
-1.750 -0.0164 0.01696 0.00994 -0.0652 1.0000 0.4502
-1.500 0.0028 0.01655 0.01027 -0.0633 1.0000 0.6568
-1.250 0.0097 0.01622 0.01047 -0.0582 1.0000 0.8454
-1.000 0.0466 0.01636 0.01038 -0.0609 0.9930 1.0000
-0.750 0.0923 0.01698 0.01060 -0.0651 0.9853 1.0000
-0.500 0.1338 0.01743 0.01077 -0.0685 0.9761 1.0000
-0.250 0.1752 0.01789 0.01099 -0.0718 0.9673 1.0000
0.000 0.2204 0.01835 0.01125 -0.0756 0.9596 1.0000
0.250 0.2573 0.01865 0.01140 -0.0779 0.9491 1.0000
0.500 0.2961 0.01895 0.01158 -0.0804 0.9393 1.0000
0.750 0.3433 0.01923 0.01175 -0.0844 0.9319 1.0000
1.000 0.3785 0.01941 0.01186 -0.0860 0.9204 1.0000
1.250 0.4154 0.01956 0.01197 -0.0880 0.9094 1.0000
1.500 0.4566 0.01964 0.01203 -0.0905 0.8998 1.0000
1.750 0.5010 0.01959 0.01198 -0.0934 0.8908 1.0000
2.000 0.5372 0.01956 0.01197 -0.0948 0.8789 1.0000
2.250 0.5760 0.01943 0.01189 -0.0965 0.8677 1.0000
2.500 0.6308 0.01884 0.01137 -0.1007 0.8614 1.0000
2.750 0.6683 0.01853 0.01114 -0.1018 0.8488 1.0000
3.000 0.7063 0.01814 0.01086 -0.1029 0.8361 1.0000
3.250 0.7449 0.01767 0.01049 -0.1039 0.8230 1.0000
3.500 0.7832 0.01715 0.01007 -0.1046 0.8087 1.0000
3.750 0.8208 0.01661 0.00966 -0.1052 0.7928 1.0000
4.000 0.8576 0.01612 0.00925 -0.1055 0.7752 1.0000
4.250 0.8857 0.01591 0.00913 -0.1046 0.7517 1.0000
4.500 0.9155 0.01568 0.00896 -0.1038 0.7265 1.0000
4.750 0.9433 0.01555 0.00890 -0.1027 0.6976 1.0000
5.000 0.9695 0.01553 0.00889 -0.1014 0.6646 1.0000
5.250 0.9936 0.01564 0.00898 -0.0998 0.6273 1.0000
5.500 1.0159 0.01588 0.00918 -0.0980 0.5852 1.0000
5.750 1.0361 0.01625 0.00945 -0.0959 0.5374 1.0000
6.000 1.0542 0.01678 0.00982 -0.0935 0.4842 1.0000
6.250 1.0702 0.01750 0.01032 -0.0911 0.4264 1.0000
6.500 1.0835 0.01841 0.01093 -0.0883 0.3620 1.0000
6.750 1.0947 0.01950 0.01168 -0.0855 0.2932 1.0000
7.000 1.1057 0.02077 0.01255 -0.0830 0.2277 1.0000
7.250 1.1168 0.02224 0.01368 -0.0806 0.1668 1.0000
7.500 1.1219 0.02460 0.01549 -0.0773 0.1011 1.0000
7.750 1.1287 0.02696 0.01755 -0.0740 0.0707 1.0000
8.000 1.1423 0.02899 0.01957 -0.0717 0.0605 1.0000
8.250 1.1618 0.03144 0.02197 -0.0703 0.0551 1.0000
8.500 1.1876 0.03370 0.02443 -0.0697 0.0513 1.0000
8.750 1.2112 0.03598 0.02675 -0.0692 0.0476 1.0000
9.000 1.2370 0.03945 0.03039 -0.0690 0.0449 1.0000
9.250 1.2571 0.04240 0.03378 -0.0677 0.0439 1.0000
9.500 1.2729 0.04585 0.03768 -0.0659 0.0436 1.0000
9.750 1.2832 0.04961 0.04191 -0.0637 0.0436 1.0000
10.000 1.2886 0.05365 0.04639 -0.0612 0.0440 1.0000
10.250 1.2897 0.05796 0.05111 -0.0586 0.0444 1.0000
10.500 1.2875 0.06266 0.05619 -0.0560 0.0450 1.0000
10.750 1.2881 0.06818 0.06198 -0.0543 0.0458 1.0000
11.000 1.2745 0.06980 0.06403 -0.0498 0.0469 1.0000
11.250 1.2366 0.07328 0.06798 -0.0448 0.0480 1.0000
11.500 1.2007 0.07829 0.07332 -0.0427 0.0491 1.0000
11.750 1.1686 0.08411 0.07941 -0.0429 0.0499 1.0000
12.000 1.1375 0.09084 0.08635 -0.0452 0.0505 1.0000
12.250 1.1058 0.09893 0.09461 -0.0498 0.0512 1.0000
12.500 1.0723 0.10922 0.10501 -0.0569 0.0520 1.0000
12.750 1.0411 0.12193 0.11776 -0.0659 0.0536 1.0000
13.000 1.0306 0.13055 0.12636 -0.0703 0.0554 1.0000
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Polar data table (+)
Polar graphs
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