EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 100,000 Max Cl/Cd: 43.74 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e559-il-100000.txt Download as CSV file: xf-e559-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 559 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6327 0.06202 0.05671 -0.0795 1.0000 0.0662
-11.000 -0.6639 0.05784 0.05248 -0.0799 1.0000 0.0659
-10.750 -0.6959 0.05465 0.04926 -0.0790 1.0000 0.0656
-10.500 -0.7212 0.05110 0.04555 -0.0786 1.0000 0.0655
-10.250 -0.7380 0.04784 0.04205 -0.0778 1.0000 0.0656
-10.000 -0.7484 0.04472 0.03860 -0.0770 1.0000 0.0661
-9.750 -0.7485 0.04183 0.03552 -0.0760 1.0000 0.0672
-9.500 -0.7391 0.04039 0.03419 -0.0746 1.0000 0.0696
-9.250 -0.7315 0.03860 0.03226 -0.0737 1.0000 0.0717
-9.000 -0.7224 0.03665 0.03005 -0.0731 1.0000 0.0745
-8.750 -0.7106 0.03461 0.02760 -0.0728 1.0000 0.0770
-8.500 -0.6971 0.03304 0.02621 -0.0717 1.0000 0.0803
-8.250 -0.6822 0.03185 0.02495 -0.0711 1.0000 0.0850
-8.000 -0.6666 0.03043 0.02342 -0.0707 1.0000 0.0910
-7.750 -0.6335 0.02903 0.02193 -0.0733 0.9958 0.1023
-7.500 -0.5898 0.02779 0.02084 -0.0779 0.9881 0.1242
-7.250 -0.5443 0.02706 0.02010 -0.0827 0.9799 0.1553
-7.000 -0.4985 0.02710 0.02023 -0.0868 0.9715 0.1808
-6.750 -0.4568 0.02709 0.02007 -0.0902 0.9613 0.2037
-6.500 -0.4174 0.02780 0.02098 -0.0923 0.9509 0.2233
-6.250 -0.3763 0.02829 0.02151 -0.0946 0.9413 0.2417
-6.000 -0.3322 0.02821 0.02140 -0.0975 0.9330 0.2577
-5.750 -0.2960 0.02797 0.02107 -0.0992 0.9222 0.2715
-5.500 -0.2470 0.02770 0.02071 -0.1029 0.9165 0.2870
-5.250 -0.2131 0.02732 0.02017 -0.1041 0.9047 0.3006
-5.000 -0.1738 0.02717 0.02003 -0.1058 0.8958 0.3128
-4.750 -0.1316 0.02684 0.01969 -0.1080 0.8880 0.3246
-4.500 -0.0914 0.02628 0.01901 -0.1101 0.8794 0.3372
-4.250 -0.0466 0.02558 0.01814 -0.1131 0.8722 0.3509
-4.000 0.0077 0.02496 0.01746 -0.1173 0.8685 0.3641
-3.750 0.0398 0.02461 0.01710 -0.1178 0.8564 0.3735
-3.500 0.0929 0.02377 0.01611 -0.1221 0.8518 0.3872
-3.250 0.1246 0.02344 0.01572 -0.1226 0.8390 0.3976
-3.000 0.1624 0.02298 0.01520 -0.1240 0.8288 0.4079
-2.750 0.2063 0.02234 0.01438 -0.1268 0.8199 0.4206
-2.500 0.2368 0.02212 0.01415 -0.1269 0.8070 0.4298
-2.250 0.2717 0.02175 0.01368 -0.1280 0.7957 0.4406
-2.000 0.3101 0.02137 0.01310 -0.1297 0.7853 0.4530
-1.750 0.3362 0.02125 0.01302 -0.1290 0.7719 0.4612
-1.500 0.3662 0.02107 0.01271 -0.1293 0.7596 0.4726
-1.250 0.3996 0.02088 0.01244 -0.1300 0.7493 0.4832
-1.000 0.4262 0.02079 0.01231 -0.1296 0.7367 0.4933
-0.750 0.4538 0.02076 0.01217 -0.1295 0.7246 0.5054
-0.500 0.4839 0.02066 0.01205 -0.1295 0.7147 0.5155
-0.250 0.5105 0.02062 0.01197 -0.1291 0.7030 0.5269
0.000 0.5371 0.02068 0.01196 -0.1289 0.6918 0.5397
0.250 0.5683 0.02059 0.01183 -0.1291 0.6831 0.5514
0.500 0.5908 0.02070 0.01199 -0.1281 0.6714 0.5631
0.750 0.6186 0.02075 0.01199 -0.1279 0.6618 0.5769
1.000 0.6461 0.02080 0.01201 -0.1277 0.6522 0.5916
1.250 0.6703 0.02094 0.01220 -0.1269 0.6425 0.6055
1.500 0.6987 0.02096 0.01220 -0.1267 0.6341 0.6213
1.750 0.7214 0.02116 0.01249 -0.1258 0.6244 0.6373
2.000 0.7507 0.02119 0.01249 -0.1257 0.6168 0.6565
2.250 0.7722 0.02145 0.01286 -0.1246 0.6074 0.6763
2.500 0.7995 0.02148 0.01292 -0.1241 0.6002 0.6984
2.750 0.8196 0.02174 0.01332 -0.1226 0.5914 0.7235
3.000 0.8449 0.02179 0.01343 -0.1217 0.5843 0.7542
3.250 0.8633 0.02201 0.01382 -0.1197 0.5768 0.7921
3.500 0.8788 0.02200 0.01399 -0.1168 0.5697 0.8460
3.750 0.9086 0.02183 0.01391 -0.1168 0.5630 1.0000
4.000 0.9385 0.02240 0.01441 -0.1182 0.5544 1.0000
4.250 0.9745 0.02272 0.01451 -0.1199 0.5486 1.0000
4.500 0.9937 0.02344 0.01530 -0.1189 0.5402 1.0000
4.750 1.0247 0.02377 0.01553 -0.1195 0.5338 1.0000
5.000 1.0474 0.02444 0.01623 -0.1189 0.5269 1.0000
5.250 1.0720 0.02498 0.01677 -0.1186 0.5200 1.0000
5.500 1.1061 0.02529 0.01693 -0.1195 0.5148 1.0000
5.750 1.1194 0.02621 0.01804 -0.1175 0.5067 1.0000
6.000 1.1489 0.02659 0.01836 -0.1178 0.5009 1.0000
6.250 1.1706 0.02732 0.01916 -0.1170 0.4945 1.0000
6.500 1.1911 0.02802 0.01992 -0.1160 0.4875 1.0000
6.750 1.2252 0.02826 0.02006 -0.1169 0.4823 1.0000
7.000 1.2359 0.02939 0.02139 -0.1146 0.4749 1.0000
7.250 1.2625 0.02980 0.02181 -0.1144 0.4686 1.0000
7.500 1.2886 0.03040 0.02241 -0.1142 0.4630 1.0000
7.750 1.3007 0.03141 0.02360 -0.1120 0.4555 1.0000
8.000 1.3349 0.03154 0.02366 -0.1128 0.4500 1.0000
8.250 1.3438 0.03277 0.02508 -0.1103 0.4428 1.0000
8.500 1.3675 0.03324 0.02560 -0.1097 0.4362 1.0000
8.750 1.3966 0.03362 0.02597 -0.1098 0.4303 1.0000
9.000 1.4020 0.03484 0.02740 -0.1068 0.4226 1.0000
9.250 1.4424 0.03458 0.02704 -0.1082 0.4166 1.0000
9.500 1.4408 0.03613 0.02885 -0.1044 0.4089 1.0000
9.750 1.4721 0.03609 0.02880 -0.1046 0.4020 1.0000
10.000 1.4828 0.03706 0.02990 -0.1023 0.3947 1.0000
10.250 1.5031 0.03740 0.03030 -0.1011 0.3870 1.0000
10.500 1.5245 0.03779 0.03074 -0.1001 0.3797 1.0000
10.750 1.5349 0.03844 0.03152 -0.0976 0.3716 1.0000
11.000 1.5608 0.03851 0.03159 -0.0971 0.3639 1.0000
11.250 1.5654 0.03928 0.03250 -0.0939 0.3557 1.0000
11.500 1.5882 0.03934 0.03257 -0.0929 0.3475 1.0000
11.750 1.5895 0.04004 0.03341 -0.0892 0.3394 1.0000
12.000 1.6054 0.04026 0.03365 -0.0873 0.3312 1.0000
12.250 1.6074 0.04089 0.03437 -0.0839 0.3229 1.0000
12.500 1.6135 0.04153 0.03507 -0.0811 0.3146 1.0000
12.750 1.6289 0.04152 0.03505 -0.0792 0.3053 1.0000
13.000 1.6138 0.04336 0.03706 -0.0748 0.2978 1.0000
13.250 1.6420 0.04272 0.03630 -0.0742 0.2872 1.0000
13.500 1.6078 0.04593 0.03982 -0.0691 0.2806 1.0000
13.750 1.6236 0.04605 0.03987 -0.0677 0.2704 1.0000
14.000 1.6024 0.04898 0.04299 -0.0646 0.2624 1.0000
14.250 1.6009 0.05065 0.04468 -0.0629 0.2531 1.0000
14.500 1.6134 0.05115 0.04506 -0.0616 0.2419 1.0000
14.750 1.5790 0.05619 0.05039 -0.0598 0.2348 1.0000
15.000 1.5810 0.05793 0.05208 -0.0588 0.2245 1.0000
15.250 1.5682 0.06139 0.05562 -0.0581 0.2152 1.0000
15.500 1.5522 0.06558 0.05990 -0.0579 0.2065 1.0000
15.750 1.5540 0.06773 0.06197 -0.0574 0.1960 1.0000
16.000 1.5346 0.07277 0.06716 -0.0579 0.1876 1.0000
16.250 1.5256 0.07672 0.07113 -0.0582 0.1787 1.0000
16.500 1.5306 0.07876 0.07301 -0.0580 0.1683 1.0000
16.750 1.5054 0.08537 0.07985 -0.0597 0.1615 1.0000
17.000 1.5065 0.08820 0.08260 -0.0599 0.1525 1.0000
17.250 1.4939 0.09324 0.08774 -0.0613 0.1451 1.0000
17.500 1.4877 0.09740 0.09192 -0.0623 0.1377 1.0000
17.750 1.4858 0.10088 0.09537 -0.0632 0.1300 1.0000
18.000 1.4733 0.10631 0.10092 -0.0651 0.1241 1.0000
18.250 1.4717 0.10988 0.10447 -0.0662 0.1172 1.0000
18.500 1.4629 0.11481 0.10949 -0.0681 0.1118 1.0000
18.750 1.4476 0.12099 0.11583 -0.0710 0.1071 1.0000
19.000 1.4569 0.12268 0.11741 -0.0712 0.1003 1.0000
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Polar data table (+)
Polar graphs
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