EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 50,000 Max Cl/Cd: 19.15 at α=12.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e642-il-50000-n5.txt Download as CSV file: xf-e642-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 642 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3371 0.10716 0.10071 -0.0569 1.0000 0.0552
-10.500 -0.3453 0.10436 0.09806 -0.0566 1.0000 0.0540
-10.250 -0.3555 0.10137 0.09521 -0.0569 0.9944 0.0529
-10.000 -0.3525 0.09493 0.08878 -0.0633 0.9804 0.0512
-9.750 -0.3907 0.08163 0.07528 -0.0787 0.9609 0.0471
-9.500 -0.3872 0.07723 0.07080 -0.0818 0.9492 0.0468
-9.250 -0.3901 0.07290 0.06634 -0.0844 0.9377 0.0464
-9.000 -0.3941 0.06904 0.06231 -0.0858 0.9273 0.0460
-8.750 -0.3986 0.06551 0.05858 -0.0861 0.9169 0.0457
-8.500 -0.4029 0.06214 0.05495 -0.0855 0.9076 0.0454
-8.250 -0.4029 0.05877 0.05127 -0.0850 0.9000 0.0451
-8.000 -0.4047 0.05595 0.04813 -0.0831 0.8916 0.0449
-7.750 -0.4003 0.05304 0.04486 -0.0817 0.8853 0.0447
-7.500 -0.3959 0.05051 0.04197 -0.0797 0.8790 0.0447
-7.250 -0.3900 0.04813 0.03920 -0.0775 0.8727 0.0448
-7.000 -0.3758 0.04561 0.03623 -0.0764 0.8683 0.0450
-6.750 -0.3663 0.04368 0.03389 -0.0740 0.8623 0.0455
-6.500 -0.3515 0.04189 0.03161 -0.0723 0.8571 0.0466
-6.250 -0.3298 0.03998 0.02945 -0.0719 0.8535 0.0485
-6.000 -0.3079 0.03855 0.02783 -0.0714 0.8499 0.0507
-5.750 -0.2912 0.03744 0.02652 -0.0698 0.8447 0.0524
-5.500 -0.2632 0.03601 0.02482 -0.0697 0.8411 0.0544
-5.250 -0.2275 0.03460 0.02309 -0.0706 0.8384 0.0573
-5.000 -0.1910 0.03335 0.02179 -0.0720 0.8362 0.0623
-4.750 -0.1720 0.03292 0.02121 -0.0707 0.8316 0.0689
-4.500 -0.1520 0.03228 0.02055 -0.0695 0.8273 0.0773
-4.250 -0.1299 0.03148 0.01971 -0.0687 0.8238 0.0930
-4.000 -0.1087 0.03034 0.01889 -0.0679 0.8209 0.1381
-3.750 -0.1096 0.02957 0.01884 -0.0639 0.8154 0.2290
-3.500 -0.1181 0.02814 0.01904 -0.0580 0.8105 0.4785
-3.250 -0.0474 0.03087 0.02231 -0.0574 0.8103 0.8326
-3.000 0.0467 0.03193 0.02272 -0.0663 0.8104 0.8927
-2.750 0.1359 0.03181 0.02205 -0.0768 0.8098 0.9270
-2.500 0.1874 0.03156 0.02146 -0.0817 0.8075 0.9456
-2.250 0.2375 0.03118 0.02079 -0.0866 0.8052 0.9588
-2.000 0.2755 0.03110 0.02050 -0.0898 0.8012 0.9702
-1.750 0.3120 0.03102 0.02024 -0.0927 0.7968 0.9802
-1.500 0.3507 0.03084 0.01989 -0.0959 0.7933 0.9886
-1.250 0.3907 0.03061 0.01949 -0.0992 0.7902 0.9959
-1.000 0.4132 0.03090 0.01968 -0.0996 0.7855 1.0000
-0.750 0.4217 0.03148 0.02019 -0.0972 0.7796 1.0000
-0.500 0.4405 0.03171 0.02033 -0.0963 0.7754 1.0000
-0.250 0.4514 0.03226 0.02082 -0.0942 0.7704 1.0000
0.000 0.4560 0.03300 0.02152 -0.0912 0.7637 1.0000
0.250 0.4753 0.03327 0.02172 -0.0902 0.7596 1.0000
0.500 0.4808 0.03401 0.02243 -0.0873 0.7534 1.0000
0.750 0.4869 0.03471 0.02311 -0.0844 0.7469 1.0000
1.000 0.5092 0.03491 0.02326 -0.0837 0.7430 1.0000
1.250 0.5027 0.03602 0.02438 -0.0791 0.7348 1.0000
1.500 0.5174 0.03646 0.02479 -0.0773 0.7294 1.0000
1.750 0.5446 0.03653 0.02482 -0.0773 0.7260 1.0000
2.000 0.5269 0.03794 0.02625 -0.0710 0.7156 1.0000
2.250 0.5511 0.03809 0.02639 -0.0705 0.7115 1.0000
2.500 0.5365 0.03936 0.02768 -0.0647 0.7014 1.0000
2.750 0.5584 0.03957 0.02788 -0.0638 0.6966 1.0000
3.000 0.5451 0.04073 0.02905 -0.0581 0.6869 1.0000
3.250 0.5648 0.04099 0.02934 -0.0569 0.6814 1.0000
3.750 0.5693 0.04232 0.03069 -0.0497 0.6657 1.0000
4.250 0.5765 0.04352 0.03193 -0.0429 0.6498 1.0000
4.750 0.5869 0.04458 0.03307 -0.0366 0.6338 1.0000
5.000 0.5735 0.04561 0.03411 -0.0313 0.6226 1.0000
5.250 0.6001 0.04550 0.03406 -0.0307 0.6178 1.0000
5.500 0.5870 0.04653 0.03510 -0.0256 0.6060 1.0000
5.750 0.6111 0.04643 0.03506 -0.0246 0.6007 1.0000
6.000 0.6049 0.04728 0.03596 -0.0205 0.5894 1.0000
6.250 0.6029 0.04810 0.03681 -0.0170 0.5785 1.0000
6.500 0.6298 0.04787 0.03666 -0.0163 0.5731 1.0000
6.750 0.6285 0.04885 0.03768 -0.0133 0.5611 1.0000
7.000 0.6360 0.04958 0.03846 -0.0113 0.5505 1.0000
7.250 0.6640 0.04925 0.03827 -0.0108 0.5443 1.0000
7.500 0.6694 0.05022 0.03931 -0.0089 0.5322 1.0000
7.750 0.6806 0.05094 0.04012 -0.0075 0.5213 1.0000
8.000 0.7117 0.05032 0.03963 -0.0071 0.5151 1.0000
8.250 0.7204 0.05123 0.04066 -0.0057 0.5025 1.0000
8.500 0.7328 0.05195 0.04148 -0.0045 0.4908 1.0000
8.750 0.7678 0.05077 0.04048 -0.0040 0.4852 1.0000
9.000 0.7781 0.05164 0.04145 -0.0028 0.4721 1.0000
9.250 0.7908 0.05234 0.04231 -0.0017 0.4598 1.0000
9.750 0.8423 0.05118 0.04147 0.0002 0.4410 1.0000
10.000 0.8564 0.05175 0.04221 0.0013 0.4277 1.0000
10.250 0.8730 0.05207 0.04268 0.0023 0.4147 1.0000
10.500 0.8932 0.05203 0.04280 0.0033 0.4018 1.0000
10.750 0.9161 0.05170 0.04262 0.0043 0.3889 1.0000
11.000 0.9386 0.05140 0.04248 0.0054 0.3748 1.0000
11.250 0.9587 0.05138 0.04258 0.0064 0.3596 1.0000
11.500 0.9758 0.05169 0.04299 0.0075 0.3431 1.0000
11.750 0.9917 0.05215 0.04353 0.0086 0.3261 1.0000
12.000 1.0069 0.05269 0.04413 0.0096 0.3087 1.0000
12.250 1.0211 0.05332 0.04479 0.0107 0.2909 1.0000
12.500 1.0294 0.05464 0.04613 0.0117 0.2734 1.0000
12.750 1.0329 0.05654 0.04809 0.0125 0.2564 1.0000
13.000 1.0359 0.05854 0.05014 0.0132 0.2396 1.0000
13.250 1.0382 0.06067 0.05230 0.0138 0.2235 1.0000
13.500 1.0397 0.06296 0.05463 0.0143 0.2080 1.0000
13.750 1.0402 0.06546 0.05716 0.0147 0.1930 1.0000
14.000 1.0396 0.06817 0.05994 0.0149 0.1786 1.0000
14.250 1.0382 0.07109 0.06290 0.0149 0.1649 1.0000
14.500 1.0361 0.07421 0.06606 0.0148 0.1517 1.0000
14.750 1.0333 0.07752 0.06940 0.0144 0.1391 1.0000
15.000 1.0281 0.08123 0.07313 0.0138 0.1267 1.0000
15.250 1.0223 0.08511 0.07700 0.0129 0.1151 1.0000
15.500 1.0154 0.08928 0.08112 0.0117 0.1041 1.0000
15.750 1.0074 0.09393 0.08586 0.0101 0.0937 1.0000
16.000 1.0005 0.09861 0.09064 0.0085 0.0846 1.0000
16.250 0.9952 0.10302 0.09506 0.0069 0.0771 1.0000
16.500 0.9902 0.10751 0.09959 0.0052 0.0702 1.0000
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Polar data table (+)
Polar graphs
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