EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 100,000 Max Cl/Cd: 55.33 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e562-il-100000-n5.txt Download as CSV file: xf-e562-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4934 0.10323 0.09775 -0.0524 1.0000 0.0295
-12.750 -0.5325 0.09127 0.08570 -0.0587 1.0000 0.0292
-12.500 -0.5623 0.08255 0.07688 -0.0634 1.0000 0.0288
-12.250 -0.5868 0.07550 0.06972 -0.0670 1.0000 0.0286
-12.000 -0.6095 0.06931 0.06340 -0.0702 1.0000 0.0285
-11.750 -0.6298 0.06398 0.05793 -0.0727 1.0000 0.0287
-11.500 -0.6460 0.05963 0.05346 -0.0742 1.0000 0.0288
-11.250 -0.6620 0.05571 0.04941 -0.0750 1.0000 0.0289
-11.000 -0.6776 0.05231 0.04589 -0.0752 1.0000 0.0291
-10.750 -0.6949 0.04939 0.04285 -0.0746 1.0000 0.0294
-10.500 -0.7145 0.04694 0.04030 -0.0729 1.0000 0.0296
-10.250 -0.7233 0.04461 0.03794 -0.0721 1.0000 0.0300
-10.000 -0.7257 0.04260 0.03590 -0.0712 1.0000 0.0305
-9.750 -0.7250 0.04079 0.03405 -0.0701 1.0000 0.0312
-9.500 -0.7217 0.03902 0.03220 -0.0691 1.0000 0.0320
-9.250 -0.7158 0.03734 0.03041 -0.0681 1.0000 0.0330
-9.000 -0.6932 0.03551 0.02836 -0.0699 0.9968 0.0347
-8.750 -0.6628 0.03369 0.02643 -0.0731 0.9916 0.0371
-8.500 -0.6313 0.03212 0.02478 -0.0762 0.9860 0.0399
-8.250 -0.5997 0.03066 0.02310 -0.0786 0.9804 0.0430
-8.000 -0.5681 0.02910 0.02153 -0.0817 0.9743 0.0471
-7.750 -0.5370 0.02776 0.02004 -0.0839 0.9678 0.0521
-7.500 -0.5033 0.02629 0.01852 -0.0869 0.9619 0.0590
-7.250 -0.4728 0.02490 0.01710 -0.0891 0.9544 0.0694
-7.000 -0.4368 0.02353 0.01572 -0.0922 0.9489 0.0866
-6.750 -0.4060 0.02237 0.01459 -0.0941 0.9409 0.1119
-6.500 -0.3690 0.02135 0.01367 -0.0970 0.9355 0.1442
-6.250 -0.3374 0.02069 0.01304 -0.0985 0.9271 0.1762
-6.000 -0.2999 0.02019 0.01255 -0.1009 0.9213 0.2122
-5.750 -0.2679 0.01988 0.01223 -0.1020 0.9127 0.2386
-5.500 -0.2305 0.01955 0.01177 -0.1040 0.9066 0.2603
-5.250 -0.1980 0.01929 0.01142 -0.1049 0.8981 0.2777
-5.000 -0.1614 0.01901 0.01105 -0.1065 0.8915 0.2941
-4.750 -0.1281 0.01876 0.01069 -0.1075 0.8830 0.3083
-4.500 -0.0915 0.01849 0.01037 -0.1089 0.8758 0.3207
-4.250 -0.0577 0.01826 0.01007 -0.1099 0.8668 0.3324
-4.000 -0.0192 0.01799 0.00969 -0.1118 0.8594 0.3453
-3.750 0.0153 0.01780 0.00938 -0.1130 0.8493 0.3583
-3.500 0.0565 0.01756 0.00907 -0.1153 0.8419 0.3705
-3.250 0.0895 0.01739 0.00884 -0.1161 0.8303 0.3800
-3.000 0.1266 0.01717 0.00850 -0.1178 0.8200 0.3911
-2.750 0.1645 0.01698 0.00824 -0.1195 0.8099 0.4008
-2.500 0.1975 0.01684 0.00802 -0.1203 0.7971 0.4103
-2.250 0.2316 0.01673 0.00780 -0.1213 0.7849 0.4207
-2.000 0.2660 0.01661 0.00763 -0.1224 0.7730 0.4298
-1.750 0.3005 0.01652 0.00741 -0.1235 0.7608 0.4406
-1.500 0.3306 0.01648 0.00734 -0.1238 0.7474 0.4493
-1.250 0.3612 0.01645 0.00723 -0.1242 0.7343 0.4593
-1.000 0.3916 0.01643 0.00714 -0.1245 0.7217 0.4690
-0.750 0.4221 0.01642 0.00707 -0.1249 0.7096 0.4785
-0.500 0.4514 0.01644 0.00700 -0.1250 0.6969 0.4893
-0.250 0.4788 0.01646 0.00703 -0.1248 0.6843 0.4981
0.000 0.5071 0.01651 0.00701 -0.1247 0.6722 0.5086
0.250 0.5355 0.01655 0.00701 -0.1247 0.6610 0.5188
0.500 0.5625 0.01661 0.00705 -0.1244 0.6491 0.5288
0.750 0.5896 0.01669 0.00710 -0.1241 0.6374 0.5402
1.000 0.6168 0.01677 0.00717 -0.1239 0.6268 0.5507
1.250 0.6436 0.01686 0.00725 -0.1235 0.6160 0.5619
1.500 0.6698 0.01697 0.00736 -0.1231 0.6049 0.5742
1.750 0.6966 0.01708 0.00746 -0.1228 0.5951 0.5866
2.000 0.7223 0.01719 0.00760 -0.1223 0.5847 0.5993
2.250 0.7482 0.01732 0.00775 -0.1218 0.5746 0.6130
2.500 0.7749 0.01745 0.00788 -0.1215 0.5656 0.6278
2.750 0.7997 0.01759 0.00809 -0.1208 0.5554 0.6439
3.000 0.8255 0.01774 0.00825 -0.1203 0.5466 0.6614
3.250 0.8499 0.01788 0.00849 -0.1195 0.5371 0.6808
3.500 0.8746 0.01804 0.00870 -0.1188 0.5284 0.7033
3.750 0.8980 0.01817 0.00892 -0.1178 0.5196 0.7282
4.000 0.9204 0.01831 0.00917 -0.1165 0.5112 0.7589
4.250 0.9411 0.01840 0.00937 -0.1149 0.5030 0.7977
4.500 0.9586 0.01845 0.00957 -0.1125 0.4949 0.8545
4.750 0.9829 0.01847 0.00968 -0.1116 0.4868 1.0000
5.000 1.0093 0.01881 0.00999 -0.1116 0.4781 1.0000
5.250 1.0358 0.01914 0.01027 -0.1115 0.4701 1.0000
5.500 1.0609 0.01950 0.01065 -0.1111 0.4618 1.0000
5.750 1.0865 0.01984 0.01097 -0.1109 0.4539 1.0000
6.000 1.1107 0.02023 0.01139 -0.1103 0.4457 1.0000
6.250 1.1356 0.02059 0.01174 -0.1099 0.4380 1.0000
6.500 1.1589 0.02099 0.01221 -0.1092 0.4298 1.0000
6.750 1.1829 0.02138 0.01259 -0.1086 0.4221 1.0000
7.000 1.2052 0.02180 0.01309 -0.1078 0.4138 1.0000
7.250 1.2283 0.02220 0.01351 -0.1071 0.4060 1.0000
7.500 1.2495 0.02265 0.01404 -0.1060 0.3975 1.0000
7.750 1.2716 0.02307 0.01447 -0.1051 0.3896 1.0000
8.000 1.2910 0.02355 0.01506 -0.1038 0.3806 1.0000
8.250 1.3122 0.02398 0.01549 -0.1028 0.3727 1.0000
8.500 1.3292 0.02449 0.01614 -0.1011 0.3631 1.0000
8.750 1.3480 0.02497 0.01664 -0.0997 0.3547 1.0000
9.000 1.3637 0.02549 0.01728 -0.0978 0.3451 1.0000
9.250 1.3786 0.02602 0.01789 -0.0958 0.3361 1.0000
9.500 1.3921 0.02656 0.01847 -0.0936 0.3269 1.0000
9.750 1.4037 0.02719 0.01923 -0.0912 0.3170 1.0000
10.000 1.4153 0.02783 0.01990 -0.0888 0.3076 1.0000
10.250 1.4248 0.02856 0.02072 -0.0863 0.2974 1.0000
10.500 1.4337 0.02937 0.02165 -0.0838 0.2871 1.0000
10.750 1.4415 0.03024 0.02255 -0.0812 0.2773 1.0000
11.000 1.4476 0.03124 0.02365 -0.0787 0.2665 1.0000
11.250 1.4528 0.03236 0.02488 -0.0762 0.2557 1.0000
11.500 1.4566 0.03363 0.02620 -0.0737 0.2451 1.0000
11.750 1.4586 0.03507 0.02767 -0.0714 0.2345 1.0000
12.000 1.4599 0.03671 0.02944 -0.0692 0.2231 1.0000
12.250 1.4598 0.03854 0.03135 -0.0672 0.2122 1.0000
12.500 1.4577 0.04066 0.03351 -0.0654 0.2015 1.0000
12.750 1.4540 0.04306 0.03595 -0.0638 0.1907 1.0000
13.000 1.4503 0.04567 0.03866 -0.0625 0.1797 1.0000
13.250 1.4447 0.04861 0.04166 -0.0615 0.1695 1.0000
13.500 1.4372 0.05190 0.04498 -0.0608 0.1601 1.0000
13.750 1.4298 0.05542 0.04858 -0.0605 0.1504 1.0000
14.000 1.4217 0.05919 0.05243 -0.0604 0.1416 1.0000
14.250 1.4111 0.06342 0.05668 -0.0607 0.1339 1.0000
14.500 1.4031 0.06761 0.06099 -0.0612 0.1257 1.0000
14.750 1.3924 0.07224 0.06564 -0.0620 0.1189 1.0000
15.000 1.3834 0.07688 0.07041 -0.0630 0.1118 1.0000
15.250 1.3728 0.08182 0.07539 -0.0642 0.1059 1.0000
15.500 1.3642 0.08668 0.08037 -0.0656 0.0995 1.0000
15.750 1.3534 0.09193 0.08561 -0.0672 0.0945 1.0000
16.000 1.3463 0.09682 0.09066 -0.0688 0.0886 1.0000
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Polar data table (+)
Polar graphs
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